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Full text of "Index of NACA technical publications, July, 1957 - September, 1958"

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NATIONAL AERONAUTICS 

ANDSEADE 

ADMINISTRATION 








RTDEX OF MCA TECHNICAL P LIB LI CATIONS 



July, 1957 - September, 1958 




WASHINGTON, 1959 



PREFACE 



This final Index of NACA Technical Publications covers the unclassi- 
fied NACA research reports issued in the period of July 1957 through 
September 1958. It is the seventh supplement to the basic 1915-1949 Index. 

Entries included herein duplicate in part the information of the index 
cards furnished with the individual research reports. Recipients main- 
taining card files may wish to discard those index cards on hand for 
unclassified research reports issued during the July 1957-September 1958 
period. Such cards were printed on salmon stock for easy identification 
in the discard process. 

The research reports declassified during this period are also 
included. A list of these reports may be found on pages 311-314. Cards 
for this list may be discarded as entries for them are included in this 
Index. Current announcement of newly declassified materials is regularly 
made in NASA PUBLICATIONS ANNOUNCEMENTS. 

The arrangement of this Index follows: (1) Outline of subject 
classification system, (2) chronological list of NACA reports under each 
subject classification, (3) list of reports declassified from July 1957 
through September 1958, (4) alphabetical index to subject categories, 
and (5) author index. 

Newly available research reports are currently announced in NASA 
PUBLICATIONS ANNOUNCEMENTS and are normally available for a 
period of 5 years after announcement. Most of the older research reports 
(those issued prior to July 1954) are thus available on a "loan only" basis, 
within the United States. Requests for NACA research reports should 
be forwarded to the address given below. 



Technical Information Division, Code BID 
National Aeronautics and Space Administration 
Washington 25, D. C. 



June 1959 



Subject 






Subject 






Heading 






Heading 






Number 


Subject Heading Outline 


Page 


Number 


Subject Heading Outline 


Page 


1 AERODYNAMICS 


1-181 


1.2.2.3.2 


Slots and Slats 


49 








1.2.2.3.3 


Leading-Edge Flaps 


49-50 


1.1 


Fundamental Aerodynamics 


3-26 


1.2.2.4 


Controls 


50-51 


1.1.1 


Incompressible Flow 


3-4 


1.2.2.4.1 


Flap Type 


51-53 


1.1.2 


Compressible Flow 


4-5 


1.2.2.4.2 


Spoilers 


53-54 


1.1.2.1 


Subsonic Flow 


5-6 


1.2.2.4.3 


All-Movable 


54-55 


1.1.2.2 


Mixed Flow 


6-7 


1.2.2.5 


Reynolds Number Effects 


55-57 


1.1.2.3 


Supersonic Flow 


7-12 


1.2.2.6 


Mach Number Effects 


57-67 


1.1.3 


Viscous Flow 


13-14 


1.2.2.7 


Wake 


67-68 


1.1.3.1 


Laminar Flow 


14-16 


1.2.2.8 


Boundary Layer 


68 


1.1.3.2 


Turbulent Flow 


16-18 


1.2.2.8.1 


Characteristics 


68 


1.1.3.3 


Jet Mixing 


18-20 


1.2.2.8.2 


Control 


69 


■1.1.4 


Aerodynamics With Heat 


20-21 








1.1.4.1 


Heating 


21 


1.3 


Bodies 


70-79 


1.1.4.2 


Heat Transfer 


22-24 


1.3.1 


Theory 


71 


1.1.4.3 


Additions of Heat 


25 


1.3.2 


Shape Variables 


72-73 


1.1.5 


Flow of Rarefied Gases 


25 


1.3.2.1 


Fineness Ratio 


73-74 


1.1.5.1 


Slip Flow 


25 


1.3.2.2 


Cross Section 


74 


1.1.5.2 


Free Molecule Flow 


25-26 


1.3.2.3 


Thickness Distribution 


74-75 


1.1.6 


Time-Dependent Flow 


26 


1.3.2.4 


Surface Conditions 


75 








1.3.2.5 


Protuberances 


75-76 


1.2 


Wings 


27-69 


1.3.3 


Canopies 


76 


1.2.1 


Wing Sections 


27 


1.3.4 


Ducted Bodies 


76 


1.2.1.1 


Section Theory 


27 


1.3.4.1 


Nose Shape 


77 


1.2.1.2 


Section Variables 


27 


1.3.4.2 


Tail Shape 


77-78 


1.2.1.2.1 


Camber 


27-28 


1.3.4.3 


Side Inlets 


78 


1.2.1.2.2 


Thickness 


28 


1.3.4.4 


Side Exits 


79 


1.2.1.2.3 


Thickness Distribution 


28-29 


*1.3.5 


Hulls 




*1. 2. 1.2.4 


Inlets and Exits 










1.2.1.2.5 


Surface Conditions 


29 


1.4 


Internal Aerodynamics 


80-97 


1.2.1.3 


Designated Profiles 


29 


1.4.1 


Air Inlets 


80 


1.2.1.4 


High-Lift Devices 


29 


1.4.1.1 


Nose, Central 


80-81 


1.2.1.4.1 


Plain Flaps 


30 


1.4.1.1.1 


Propeller-Spinner- 




1.2.1.4.2 


Split Flaps 


30 




Cowl Combinations 


81 


1.2.1.4.3 


Slotted Flaps 


30 


1.4.1.1.2 


Subsonic 


81 


1.2.1.4.4 


Leading-Edge Flaps 


30 


1.4.1.1.3 


Supersonic 


81-82 


1.2.1.4.5 


Slots and Slats 


30 


1.4.1.2 


Nose, Annular 


82-83 


1.2.1.5 


Controls 


30 


1.4.1.3 


Wing-Leading-Edge 


83 


1.2.1.5.1 


Flap Type 


30-31 


1.4.1.4 


Side 


83-84 


1.2.1.5.2 


Spoilers 


31 


1.4.1.4.1 


Scoops 


84-85 


1.2.1.6 


Boundary Layer 


31 


*1. 4. 1.4.2 


Submerged 




1.2.1.6.1 


Characteristics 


31 


1.4.2 


Ducts 


85-86 


1.2.1.6.2 


Control 


32 


1.4.2.1 


D iff users 


86 


1.2.1.7 


Reynolds Number Effects 


32 


1.4.2.1.1 


Subsonic 


86-87 


1.2.1.8 


Mach Number Effects 


32-33 


1.4.2.1.2 


Supersonic 


87-89 


1.2.1.9 


Wake 


33 


1.4.2.2 


Nozzles 


89-90 


1.2.2 


Complete Wings 


33 


1.4.2.3 


Pipes 


90-91 


1.2.2.1 


Wing Theory 


33-34 


1.4.2.4 


Bends 


91 


1.2.2.2 


Wing Variables 


34-35 


1.4.3 


Exits 


91-93 


1.2.2.2.1 


Profiles 


35-37 


1.4.4 


Jet Pumps and Thrust 




1.2.2.2.2 


Aspect Ratio 


37-39 




Augmenters 


93 


1.2.2.2.3 


Sweep 


39-44 


1.4.5 


Cascades 


93-94 


1.2.2.2.4 


Taper and Twist 


44-45 


1.4.5.1 


Theory 


94 


1.2.2.2.5 


Inlets and Exits 


45 


1.4.5.2 


Experiment 


95 


1.2.2.2.6 


Surface Conditions 


45 


1.4.6 


Fans 


95-96 


1.2.2.2.7 


Dihedral 


45-46 


1.4.7 


Boundary Layer 


96 


1.2.2.3 


High-Lift Devices 


46-47 


1.4.7.1 


Characteristics 


96-97 


1.2.2.3.1 


Trailing-Edge Flaps 


47-49 


1.4.7.2 


Control 


97 


*No reports under this category for this period. 

iii 









Subject 






Subject 






Heading 






Heading 






Number 


Subject Heading Outline 


Page 


Number 


Subject Heading Outline 


Page 


i.5 


Propellers 


98-102 


1.8.1 


Stability 


132 


1.5.1 


Theory 


98 


1.8.1.1 


Static 


132-133 


1.5.2 


Design Variables 


98 


1.8.1.1.1 


Longitudinal 


133-144 


1.5.2.1 


Blade Sections 


98 


1.8.1.1.2 


Lateral 


144-148 


1.5.2.2 


Solidity 


99 


1.8.1.1.3 


Directional 


148-151 


*1. 5.2.3 


Pitch Distribution 




1.8.1.2 


Dynamic 


151-152 


1.5.2.4 


Blade Plan Forms 


99 


1.8,1.2.1 


Longitudinal 


152-155 


1.5.2.5 


Mach Number Effects 


99 


1.8.1.2.2 


Lateral and 




*1.5.2.6 


Pusher 






Directional 


155-157 


1.5.2.7 


Dual Rotation 


99-100 


1.8.1.2.3 


Damping Derivatives 


157-160 


1.5.2.8 


Interference of Bodies 


100 


1.8.2 


Control 


160 


1.5.2.9 


Pitch and Yaw 


100 


1.8.2.1 


Longitudinal 


160-166 


*1.5.2.10 


Diameter 




1.8.2.2 


Lateral 


166-169 


1.5.3 


Designated Types 


100 


1.8.2.3 


Directional 


169-170 


1.5.4 


Slipstream 


100-101 


1.8.2.4 


Air Brakes 


170 


*1.5.5 


Selection Charts 




1.8.2.5 


Hinge Moments 


170-172 


1.5.6 


Operating Conditions 


101 


1.8.2.6 


Automatic 


172 


1.5.7 


Propeller-Spinner- 




1.8.2.7 


Jet Reaction 


173 




Cowl Combinations 


101-102 


1.8.3 


Spinning 


173 








1.8.4 


Stalling 


173-174 


1.6 


Rotating Wings 


103-104 


1.8.5 


Flying Qualities 


174-176 


1.6.1 


Theory 


103 


1.8.6 


Mass and Gyroscopic 




1.6.2 


Experimental Studies 


103 




Problems 


176-177 


1.6.2.1 


Power -Driven 


103 


*1.8.7 


Tumbling 




1.6.2.2 


Autorotating 


104 


1.8.8 


Automatic Stabilization 


177-178 








1.8.9 


Tracking 


178 


1.7 


Aircraft 


105-131 








1.7.1 




105 


1.9 


Aeroelasticity 


179-180 


1.7.1.1 


Components in 












Combination 


105-107 


1.10 


Parachutes 


181 


1.7.1.1.1 


Wing- Fuselage 


107-112 








1.7.1.1.2 


Wing-Nacelle 


112-113 








1.7.1.1.3 


Tail-Wing and 
Fuselage 


113-116 


2 1 


HYDRODYNAMICS 


183-191 


1.7.1.1.4 


Propeller and Jet 
Interference 


117 


2.1 


Theory 


184 


1.7.1.1.5 


Stores 


117-118 


2.2 


General Arrangement 




1.7.1.1.6 


Jet Interference 


118 




Studies 


185 


1.7.1.2 


Specific Airplanes 


118-123 








1.7.1.3 


Performance 


123 


2.3 


Seaplane Hull Variables 


186 


1.7.2 


Missiles 


124 


2.3.1 


Length-Beam Ratio 


186 


1.7.2.1 


Components in 




2.3.2 


Dead Rise 


186 




Combination 


124-126 


*2.3.3 


Steps 




1.7.2.1.1 


Wing-Body 


126-127 


*2.3.4 


Afterbody Shape 




1.7.2.1.2 


Tail-Body 


127 


2.3.5 


Forebody Shape 


186 


1.7.2.1.3 


Jet Interference 


128 


2.3.6 


Chines 


186 


1.7.2.1.4 


Wing-Tail-Body 


129 








1.7.2.2 


Specific Missiles 


129-130 


*2.4 


Specific Seaplanes and 




1.7.3 


Rotating-Wing Aircraft 


130 




Hulls 




1.7.3.1 


Autogiros 


130 








1.7.3.2 


Helicopters 


130-131 


*2.5 


Lateral Stabilizers 




*1.7.4 


Seaplanes 




*2.5.1 


Wing-Tip Float 




*1. 7.4.1 


General Studies 










*1. 7.4.2 


Specific Types 




2.6 


Planing Surfaces 


187 


1.7.5 


Airships 


131 








*1.7.6 


Biplanes and Triplanes 




2.7 


Hydrofoils 


188 


1.8 


Stability and Control 


132-178 


2.8 


Surface Craft 


189 



No reports under this category for this period. 



IV 



Subject 






Subject 






Heading 






Heading 






Number 


Subject Heading Outline 


Page 


Number 


Subject Heading Outline 


Page 


2.9 


Ditching Characteristics 


190 


3.3.2.1 


Liquid Injection 


205 








3.3.2.2 


Afterburning 


205-206 


2.10 


Stability and Control 


191 


♦3.3.2.3 


Bleedoff 




*2.10.1 


Longitudinal 




3.3.3 


Rocket Assist 


206 


*2.10.2 


Lateral 










*2.10.3 


Directional 




3.4 


Fuels 


207-212 








3.4.1 


Preparation 


207 








3.4.2 


Physical and Chemical 




3 


PROPULSION 


193-244 


3.4.3 


Properties 
Relation to Engine 


207-208 


3.1 


Complete Systems 


194-202 




Performance 


209 


*3.1.1 


Reciprocating Engines 




*3.4.3.1 


Reciprocating Engines 




*3. 1.1.1 


Spark-Ignition Engines 




♦3.4.3.1.1 


Spark-Ignition 




*3. 1.1.2 


Compression-Ignition 
(Diesel) Engines 




*3. 4.3. 1.2 


Compression-Ignition 
(Diesel) Engines 




♦3.1.2 


Reciprocating Engines - 




3.4.3.2 


Turbine Engines, Ram 






Turbines 






Jets, and Pulse Jets 


209-210 


*3. 1.2.1 


Turbosupercharged 




3.4.3.3 


Rockets (Includes Fuel 






Engines 






and Oxidant) 


211-212 


*3. 1.2.2 


Compound Engines 










*3. 1.2.3 


Gas Generator - Turbine 


3.5 


Combustion and 






Engines 






Combustors 


213-222 


3.1.3 


Turbojet Engines 


194-197 


3.5.1 


General Combustion 




3.1.4 


Turbo-Propeller Engines 


197 




Research 


213-214 


♦3.1.5 


Ducted Propeller Engines 




3.5.1.1 


Laminar-Flow 




♦3.1. 6 


Pulse-Jet Engines 






Combustion 


214 


3.1.7 


Ram-Jet Engines 


198-199 


3.5.1.2 


Turbulent-Flow 




3.1.8 


Rocket Engines 


199-201 




Combustion 


215 


3.1.9 


Jet -Driven Rotors 


201 


3.5.1.3 


Detonation 


215 


3.1.10 


Nuclear Energy Systems 


201 


3.5.1.4 


Effects of Fuel 




3.1.11 


Miscellaneous Engines 


201-202 




Atomization 


215-216 


*3.1.12 


Comparison of Engine 




3.5.1.5 


Reaction Mechanisms 


216 




Types 




3.5.1.6 


Ignition of Gases 


216-217 








3.5.2 


Effect of Engine Operating 


3.2 


Control of Engines 


203-204 




Conditions and Combustion- 


*3.2.1 


Charging and Control of 






Chamber Geometry 


217-218 




Reciprocating Engines 




*3.5.2.1 


Reciprocating Engines 




*3.2.1.1 


Spark-Ignition Engines 




♦3.5.2.1.1 


Spark-Ignition Engines 


♦3.2.1.2 


Compression-Ignition 
Engines 




*3.5.2.1.2 


Compression-Ignition 
(Diesel) Engines 




♦3.2.1.3 


Compound Engines 




3.5.2.2 


Turbine Engines 


218-219 


3.2.2 


Control of Turbojet 




3.5.2.3 


Ram -Jet Engines 


219-220 




Engines 


203 


*3.5.2.4 


Pulse-Jet Engines 




♦3.2.3 


Control of Turbine-Ram- 
Jet Engines 




3.5.2.5 


Rocket Engines 


221-222 


3.2.4 


Control of Turbine- 




3.6 


Compression and 






Propeller Engines 


203 




Compressors 


223-229 


♦3.2.5 


Control of Pulse-Jet 




3.6.1 


Flow Theory and 






Engines 






Experiment 


223-224 


3.2.6 


Control of Ram -Jet 




3.6.1.1 


Axial-Flow 


224-228 




Engines 


203-204 


3.6.1.2 


Radial- Flow 


228 


3.2.7 


Control of Rocket Engines 204 


3.6.1.3 


Mixed-Flow 


228 


*3.2.8 


Control of Gas Generator 




♦3.6.1.4 


Positive Displacement 






Engines 




3.6.2 


Stress and Vibration 


228-229 








3.6.3 


Matching 


229 


*il* 


Auxiliary Booster Systems 


205-206 








3.3.1 


Reciprocating Engines 




3.7 


Turbines 


230-233 


♦3.3.2 


Gas Turbines 




3.7.1 


Flow Theory and Experiment 230 


No reports under this category for this period. 

V 









Subject 






Subject 






Heading 






Heading 






Number 


Subject Heading Outline 


Page 


Number 


Subject Heading Outline 


Page 


3.7.1.1 


Axial- Flow 


230-231 


3.12.1.5 


Turbine-Propeller Engines 242 


♦3.7.1.2 


Radial- Flow 




♦3.12.1.6 


Pulse-Jet Engines 




3.7.1=3 


Mixed-Flow 


231 


3.12.1.7 


Ram-Jet Engines 


242 


3.7.2 


Cooling 


232-233 


3.12.1.8 


Rocket Engines 


242 


3.7.3 


Stress and Vibration 


233 


3.12.1.8.1 


Turbopump 


242-243 


3.7.4 


Matching 


233 


3.12.2 


Ignition Systems 


243 








3.12.3 


Starting Systems 


243 


3.8 


Friction and Lubrication 


234-235 


♦3.12.4 


Lubrication Systems 




3.8.1 


Theory and Experiment 


234 


3.12.5 


Cooling Systems 


243 


3.8.1.1 


Hydrodynamic Theory 


234 








3.8.1.2 


Chemistry of 
Lubrication 


234 


3.13 


Vibration and Flutter 


244 


♦3.8.1.3 


Surface Conditions 










3.8.2 
♦3.8.2.1 


Sliding Contact Surfaces 
Sleeve Bearings 


234 


4 AIRCRAFT LOADS AND 
CONSTRUCTION 


245-267 


♦3.8.2.2 


Cylinder and Piston 












Mechanisms 




4.1 


Loads 


245 


*3.8.2.3 


Slipper Plate 




4.1.1 


Aerodynamic 


245 


♦3.8.2.4 


Kingsbury and Mitchell 




4.1.1.1 


Wings 


245-247 




Bearings 




4.1.1.1.1 


Steady Loads 


247-249 


3.8.3 


Rolling Contact Surfaces 


234 


4.1.1.1.2 


Maneuvering 


249-250 
250 


3.8.3.1 


Antifriction Bearings 


234-235 


4.1.1.1.3 


Gust Loads 


3.8.4 


Sliding and Rolling 




4.1.1.1.4 


Buffeting Loads 


251 
251 




Contact Surfaces 


235 


4.1.1.2 


Tail 


♦3.8.4.1 


Gears 




4.1.1.2.1 


Steady Loads 


252 


3.8.5 


Lubricants 


235 


4.1.1.2.2 


Maneuvering 


252 








4.1.1.2.3 


Buffeting and Gust 


252 


3.9 


Heat Transfer 


236-238 


4.1.1.3 


Bodies 


253-254 


3.9.1 


Theory and Experiment 


236-237 


4.1.1.4 


Rotating Wings 


254 


3.9.1.1 


Cascades 


237 


4.1.1.5 


Aeroelasticity 


254-255 


3.9.2 


Heat Exchangers 


237-238 


4.1.2 


Landing 


255 


♦3.9.2.1 


Radiators 




4.1.2.1 


Impact 


255-256 


♦3.9.2.2 


Intercoolers 




4.1.2.1.1 


Land 


256 


3.9.2.3 


Aftercoolers 


238 


4.1.2.1.2 


Water 


256 


*3.9.2.4 


Regenerators 




4.1.2.2 


Ground -Run 


256 


♦3.9.2.5 


Oil Coolers 




4.1.2.2.1 


Land 


256-257 








4.1.2.2.2 


Water 


257 


3.10 


Cooling of Engines 


239-240 


♦4.1.2.3 


Prelanding Conditions 




♦3.10.1 


Reciprocating Engines 










♦3.10.1.1 


Liquid-Cooled 




4.2 


Vibration and Flutter 


258-267 


♦3.10.1.2 


Air-Cooled 




4.2.1 


Wings and Ailerons 


258-259 


3.10.2 


Gas-Turbine Systems 


239-240 


4.2.2 


Tails 


259 


♦3.10.3 


Ram Jets 




4.2.2.1 


Elevators and Rudders 


, 259 


♦3.10.4 


Pulse Jets 




♦4.2.2.2 


Tabs 




3.10.5 


Rockets 


240 


4.2.3 
4.2.4 


Bodies 

Propellers, Fans, and 


259 


3.11 


Properties of Gases 
Kinetic 


241 




Compressors 


259-260 


3.11. 1 


241 


4.2.5 


Rotating-Wing Aircraft 


260 


3.11.2 


Thermodynamic 


241 


4.2.6 


Panels and Surface 
Coverings 


260 


3.12 


Accessories and Accessory 






261-267 




Functions 


242-243 


4.3 


Structures 


3.12.1 


Fuel Systems 


242 


4.3.1 


Columns 


261 
261 


♦3.12.1.1 


Spark-Ignition Engines 


i 


4.3.1.1 


Tubular 


♦3.12.1.2 


Compression -Ignition 




♦4.3.1.2 


Beams 


261 




Engines 




4.3.1.3 


Sections 


♦3.12.1.3 


Compound Engines 




♦4.3.2 


Frames, Gridworks, and 


3.12.1.4 


Turbojet Engines 


242 




Trusses 





+ No reports under this category for this period. 



vi 



Subject 






Subject 








Heading 






Heading 








Number 


Subject Heading Outline 


Page 


Number 


Subject Heading Outline 


Page 


4.3.3 


Plates 


261 


5.2.6 


Shear 




276 


4.3.3.1 


Flat 


261 


5.2.7 


Flexural 




276 


4.3.3.1.1 


Unstiffened 


262 


5.2.8 


Corrosion Resistance 


276 


-277 


4.3.3.1.2 


Stiffened 


262 


5.2.9 


Structure 




277 


4.3.3.2 


Curved 


262 


♦5.2.10 


Effects of Nuclear Radiation 




4.3.3.2.1 


Unstiffened 


262 


5.2.11 


Thermal 


277 


-278 


4.3.3.2.2 


Stiffened 


262 


5.2.12 


Multiaxial Stress 




278 


4.3.4 


Beams 


262 


5.2.13 


Plasticity 




278 


4.3.4.1 


Box 


262-263 










♦4.3.4.2 


Diagonal Tension 




5.3 


Operating Stresses and 






4.3.5 


Shells 


263 




Conditions 




279 


4.3.5.1 


Cylinders 


263 


♦5.3.1 


Airframe 






4.3.5.1.1 


Circular 


263 


5.3.2 


Propulsion System 




279 


♦4.3.5.1.2 


Elliptical 












♦4.3.5.2 


Boxes 












4.3.6 


Connections 


263 


6 


METEOROLOGY 


281 


-283 


*4. 3.6.1 


Bolted 












4.3.6.2 


Riveted 


264 


6.1 


Atmosphere 




281 


♦4.3.6.3 


Welded 




*6.1.1 


Standard Atmosphere 






4.3.6.4 


Bonded 


264 


6.1.2 


Gusts 




281 


4.3.7 


Loads and Stresses 


264 


6.1.2.1 


Structure 




281 


♦4.3.7.1 


Tension 




6.1.2.2 


Frequency 




281 


4.3.7.2 


Compression 


264-265 


6.1.2.3 


Turbulence 


281 


-282 


4.3.7.3 


Bending 


265 


6.1.2.4 


Alleviation 




282 


4.3.7.4 


Torsion 


265 


6.1.3 


Electricity 




282 


4.3.7.5 


Shear 


265 










4.3.7.6 


Concentrated 


265 


6.2 


Ice Formation 




283 


4.3.7.7 


Dynamic 


265-266 










4.3.7.7.1 


Repeated 


266 










4.3.7.7.2 


Transient 


266-267 


7 


OPERATING PROBLEMS 


285 


-294 


4.3.7.8 


Normal Pressures 


267 










4.3.8 


Weight Analysis 


267 


7.1 
7.1.1 


Safety 
Pilot-Escape Techniques 




286 
286 


5 MATERIALS 


269-279 


7.2 


Navigation 




287 


5.1 


Types 


270 


7.3 


Ice Prevention and Removal 


288 


5.1.1 


Aluminum 


270 


7.3.1 


Engine Induction Systems 




288 


5.1.2 


Magnesium 


270 


7.3.2 


Propellers 




288 


5.1.3 


Steels 


270-271 


7.3.3 


Wings and Tails 




288 


5.1.4 


Heat-Resisting Alloys 


271-272 


♦7.3.4 


Windshields 






♦5.1.5 


Ceramics 




7.3.5 


Miscellaneous Accessories 


288 


5.1.6 


Plastics 


272 


7.3.6 


Propulsion Systems 




288 


♦5.1.7 


Woods 












5.1.8 


Adhesive s 


272 


7.4 


Noise 




289 


5.1.9 


Protective Coatings 


272 










*5.1.10 


Fabrics 




*7.5 


Heating and Ventilating 






5.1.11 


Sandwich and Laminates 


272 










5.1.12 


Ceramals 


272 


7.6 


Lightning Hazards 




290 


♦5.1.13 


Titanium 




7.7 


Piloting Techniques 




291 


5.2 


Properties 


273-279 










5.2.1 


Tensile 


273 


7.8 


Physiological 




292 


5.2.2 


Compressive 


273 










5.2.3 


Creep 


273-274 


7.9 


Fire Hazards 




293 


5.2.4 


Stress-Rupture 


274-275 










5.2.5 


Fatigue 


275-276 


7.10 


General 




294 


No reports under this category for this period. 














vii 











Subject 

Heading 

Number Subject Heading Outline Page 

8 INSTRUMENTS 295-298 

8.1 Flight 296 

8.2 Laboratory 297 

8. 3 Meteorological 298 



9 


RESEARCH EQUIPMENT 






AND TECHNIQUES 


299-308 


9.1 


Equipment 


300 


9.1.1 


Wind Tunnels 


300-301 


9.1.2 


Free-Flight 


301-302 


9.1.3 


Towing Tanks and 
Impact Basins 




9.1.4 


Propulsion Research 






Equipment 


302 


9.1.5 


Propeller 


302 



Subject 






Heading 






Number 


Subject Heading Outline 


Page 


9.1.6 


Materials 


302 


9.1.7 


Structures 


302 


9.2 


Technique 


303 


9.2.1 


Corrections 


303-304 


9.2.2 


Aerodynamics 


304-306 


9.2.3 


Hydr ody uamic s 


306 


9.2.4 


Loads and Construction 


306-307 


9.2.5 


Propulsion 


307 


9.2.6 


Operating Problems 


307 


9.2.7 


Mathematics 


307-308 



*10 



*11 



12 



NOMENCLATURE 



BIBLIOGRAPHIES AND INDEXES 



TECHNICAL SUMMARIES 309 



*No reports under this category for this period. 



viii 




(1) 

AERODYNAMICS 



(1) AERODYNAMICS 



(i) 

AERODYNAMICS 



DESIGN PROCEDURE AND LIMITED TEST RE- 
SULTS FOR A HIGH SOLIDITY, 12-INCH TRAN- 
SONIC IMPELLER WITH AXIAL DISCHARGE. 
LinwoodC. Wright and Karl Kovach. April 1953. 
37p. photos., diagrs., tab. (NACA RM E53B09) 



COMPOSITION AND THERMODYNAMIC PROPER- 
TIES OF AIR IN CHEMICAL EQUILIBRIUM. W. E. 
Moeckel and Kenneth C. Weston. April 1958. 39p. 
diagrs. (NACA TN 42G5) 



(1) AERODYNAMICS 



(U) 

Fundamental Aerodynamics 



EXPERIMENTAL INVESTIGATION OF DRAG OF 
AFTERBODIES WITH EXITING JET AT HIGH 
SUBSONIC MACH NUMBERS. Reino J. Salmi. 
November 1354. 28p. diagrs., photos. 
(NACA RM E54I13) 



A PRELIMINARY INVESTIGATION OF STATIC- 
PRESSURE CHANGES ASSOCIATED WITH COMBUS- 
TION OF ALUMINUM BOROHYDRIDE IN A SUPER- 
SONIC WIND TUNNEL. Robert G. Dorsch, John S. 
Serafini, and Edward A. Tletcher. August 1955, 
12p. diagrs., ph'.tos. (NACA RM E55F07) ' 



ON THE SPECTRUM OF NATURAL OSCILLATIONS 
OF TWO-DIMENSIONAL LAMINAR FLOWS. (Uber 
das Spektrum bei Eigenschwingungen ebener 
Laminarstromungen. ) D. Grohne. December 1957. 
34p. diagrs. (NACA TM 1417. Translation from 
Zeitschrift fiir angewandte Mathematik und 
Mechanik, v. 34, no. 8-9, August -September 1954, 
p. 344-357) 



COMPILATION OF INFORMATION ON THE TRAN- 
SONIC ATTACHMENT OF FLOWS AT THE LEAD- 
ING EDGES OF AIRFOILS. Walter F. Lindsey and 
Emma Jean Landrum. February 1958. 63p. 
diagrs., photos., tabs. (NACA TN 4204) 



APPROXIMATIONS FOR THE THERMODYNAMIC 
AND TRANSPORT PROPERTIES OF HIGH- 
TEMPERATURE AIR. C Frederick Hansen. 
March 1958. 67p. dUgre., tabs. (NACA TN 4150) 



AN APPROXIMATE ANALYTICAL METHOD FOR 
STUDYING ENTRY INTO PLANETARY ATMOS- 
PHERES. Dean R. Chapman. May 1958. (i), lOlp. 
diagrs., tab. (NACA TN 4276) 



ON FULLY DEVELOPED CHANNEL FLOWS: SOME 
SOLUTIONS AND LIMITATIONS, AND EFFECTS OF 
COMPRESSIBILITY, VARIABLE PROPERTIES, .< 
AND BODY FORCES. Stephen H. Maslen. September 
1958. 46p. diagrs., tabs. (NACA TN 4319) 



(1.1.1) 
INCOMPRESSIBLE FLOW 



DETERMINATION OF VORTEX PATJIS BY SERIES 
EXPANSION TECHNIQUE WITH APPLICATION TO 
CRUCIFORM WINGS- Alberta Y. Alksne. 1957. 
iii, 13p. diagrs., photos. (NACA Rept. 1311. 
Supersedes TN 3670) 



INDUCED VELOCITIES NEAR A LIFTING ROTOR 
WITH NONUNIFORM DISK LOADING. Harry H. 
HeysonandS. Katzoff. 1957. iii, 88p. diagrs., 
photos., tab. (NACA Rept. 1319. Supersedes 
TN 3690; TN 3691) 



THEORETICAL AND EXPERIMENTAL INVESTIGA- 
TION OF THE SUBSONIC-FLOW FIELDS BENEATH 
SWEPT AND UNSWEPT WINGS WITH TABLES OF 
VORTEX -INDUCED VELOCITIES. William J. 
Alford, Jr. 1957. ii, 43p. diagrs., photo., tabs. 
(NACA Rept. 1327. Supersedes TN 3738) 



THEORETICAL ANALYSIS OF TOTAL -PRESSURE 
LOSS AND AIRFLOW DISTRIBUTION FOR TUBULAR 
TURBOJET COMBUSTORS WITH CONSTANT ANNU- 
LUS AND LINER CROSS-SECTIONAL AREAS. 
Charles C. Graves and Jack S. Grobman. January 
1957. 85p. diagrs., tab. (NACA RM E56I04) 



INFLUENCE OF TURBULENCE ON TRANSFER OF 
HEAT FROM CYLINDERS. J. Kestln and P. F. 
Maeder, Brown University. October 1957. 78p. 
diagrs., tabs. (NACA TN 4018) 



EFFECT OF FLOW INCIDENCE AND REYNOLDS 
NUMBER ON LOW-SPEED AERODYNAMIC CHAR- 
ACTERISTICS OF SEVERAL NONCIRCULAR CYL- 
INDERS WITH APPLICATIONS TO DIRECTIONAL 
STABILITY AND SPINNING. Edward C. Polhamus. 
January 1958. 54p. diagrs., photo., t** 
(NACA TN 4176) 



TURBULENT FLOW THROUGH POROUS RESIST- 
ANCES SLIGHTLY INCUNED TO THE FLOW 
DIRECTION. Albert L. Loeffler, Jr., and Morris 
Perlmutter. February 1958. 30p. diagrs., photos. 
(NACA TN 4221) 



SKIN-FRICTION MEASUREMENTS IN INCOMPRES- 
SIBLE FLOW. Donald W. Smith and John H. Walker. 
March 1958. 67p. diagrs., photo., tabs. 
(NACA TN 4231) 



TURBULENT SHEARING STRESS IN THE BOUND- 
ARY LAYER OF YAWED FLAT PLATES. 
Harry Ashkenas, Cornell University. April 1958. 
58p. diagrs., photos., tab. (NACA TN 4140) 



AN APPROXIMATE METHOD FOR DESIGN OR 
ANALYSIS OF TWO-DIMENSIONAL SUBSONIC- 
FLOW PASSAGES. E. Floyd Valentine. April 
1958. 38p. diagrs., photo. (NACA TN 4241) 



GENERAL SOLUTIONS FOR FLOW PAST SLENDER 
CAMBERED WINGS WITH SWEPT TRAILING EDGES 
AND CALCULATION OF ADDITIONAL LOADING 
DUE TO CONTROL SURFACES. E. B. Klunker 
and Keith C, Harder. May 1958. 55p. diagrs. 
(NACA TN 4242) 



ELLIPTIC FUNCTIONS AND INTEGRALS WITH 
REAL MODULUS IN FLUID MECHANICS. (Les 
Functions et Integrates Elliptiques a Module Reel en 
Mecanique des Fluides). Robert Legendre, June 
1958. 113p. diagrs., (NACA TM 1435. Translation 
of Office National d'Etudes et de Recherches 
Aeronautiques, Publication 71, 1954) 



(1) AERODYNAMICS 



AERODYNAMIC RESEARCH ON FUSELAGES WITH 
RECTANGULAR CROSS SECTION. (Aerodynamische 
Untersuchungen an Rumpfen mit rechteckahnlichem 
Querschnitt.) K. Maruhn. July 1958. 37p. diagrs. 
(NACA TM 1414. Translation from Jahrbuch 1942 
derdeutschen Luftfahrtforschung, p. 263-279.) 



BOUNDARY -LAYER STABILITY DIAGRAMS FOR 
ELECTRICALLY CONDUCTING FLUIDS IN THE 
PRESENCE OF A MAGNETIC FIELD. Vernon J. 
Rossow. August 1958. 32p. diagrs., tabs. 
(NACA TN 4282) 



SOME NUMERICAL SOLUTIONS OF SIMILARITY 
EQUATIONS FOR THREE-DIMENSIONAL LAMINAR 
INCOMPRESSIBLE BOUNDARY -LAYER FLOWS. 
Peggy L. Yohner and Arthur G. Hansen. September 
1958. 76p. diagrs., tabs. (NACA TN 4370) 



ANALYSIS OF TURBULENT FLOW AND HEAT 
TRANSFER IN NONCIRCULAR PASSAGES. Robert 
G. Deisster and Maynard F. Taylor. September 
1958. 35p. diagrs. (NACA TN 4384) 



(1.1.2) 
COMPRESSIBLE FLOW 



INVESTIGATION OF PRESSURE RECOVERY OF A 
SINGLE-CONICAL-SHOCK NOSE INLET AT MACH 

NLMBER 5.4. Harry Bernstein and Rudolph C. 
HaefelL April 1953. 22p. diagrs., photos. 
(NACA RM E53A12) 



DESIGN PROCEDURE AND LIMITED TEST RE- 
SULTS FOR A HIGH SOLIDITY, 12-INCH TRAN- 
SONIC IMPELLER WITH AXIAL DISCHARGE. 
Einwood C. Wright and Karl Kovach. April 1953. 
37p. photos., diagrs., tab. (NACA RM E53B09) 



INVESTIGATION OF WING FLUTTER AT TRAN- 
SONIC SPEEDS FOR SIX SYSTEMATICALLY VARIED 
WING PLAN FORMS. George W. Jones, Jr., and 
Hugh C. DuBose. August 1953. 32p. diagrs., 
photos., 3 tabs. (NACA RM L53G10a) 



PUMPING AND THRUST CHARACTERISTICS OF 
SEVERAL DIVERGENT COOLING-AIR EJECTORS 
AND COMPARISON OF PERFORMANCE WITH CON- 
ICAL AND CYLINDRICAL EJECTORS. S. C. 

Huntley and Herbert Yanowitz, January 1954. 42p. 
diagrs. (NACA RM E53J13) 



GENERAL CONSIDERATIONS OF MACH NUMBER 
EFFECTS ON COMPRESSOR-BLADE DESIGN. 
John F. Klapproth. April 1954. 24p. diagrs., 
photos. (NACA RM E53L23a) 



PRELIMINARY INVESTIGATION OF PUMPING AND 
THRUST CHARACTERISTICS OF FULL-SIZE 
COOLING-AIR EJECTORS AT SEVERAL EXHAUST- 
GAS TEMPERATURES. W. K. Greathouse. April 
1954. 130p. diagrs., photos., tab. 
(NACA RM E54A18) 



EXPERIMENTAL DATA FOR FOUR FULL-SCALE 
CONICAL COOLING-AIR EJECTORS. C. C. 
Ciepluth and D. B. Fenn. November 1954. 4lp. 
diagrs., photo., tab. (NACA RM E54F02) 



INVESTIGATION OF COMPRESSIBLE FLOW 
MIXING LOSSES OBTAINED DOWNSTREAM OF A 
BLADE ROW. Warner L. Stewart. December 1954. 
2lp. diagrs. (NACA RM E 541 20) 



PRELIMINARY FLIGHT-DETERMINED PRESSURE 
DISTRIBUTIONS OVER THE WING OF THE 
DOUGLAS X-3 RESEARCH AIRPLANE AT SUBSONIC 
AND TRANSONIC MACH NUMBERS. Gareth H. 
Jordan and C. Kenneth Hutchins, Jr. April 1955. 
34p. diagrs., photos., tabs. (NACA RM H55A10) 



PRELIMINARY ATTEMPTS AT ISOTHERMAL COM- 
PRESSION OF A SUPERSONIC AIR STREAM. 
E. Perchonok andF. Wilcox. January 1956. 33p. 
diagrs., photos., tab. (NACA RM E55I29a) 



A METHOD FOR THE DESIGN OF POROUS-WALL 
WIND TUNNELS. George M. Stokes. January 
1956. 5 Op. diagrs., photo., tabs. 
(NACA RM L55J13a) 



EXPERIMENTAL INVESTIGATION OF INTERFER- 
ENCE EFFECTS OF LATERAL-SUPPORT STRUTS 
ON AFTERBODY PRESSURES AT MACH 1.9. John 
L. Klann and Ronald G. Huff. May 1956. 13p. 
diagrs., tab. (NACA RM E56C16) 



AVERAGE PROPERTIES OF COMPRESSIBLE LAM- 
INAR BOUNDARY LAYER ON FLAT PLATE WITH 
UNSTEADY FLIGHT VELOCITY. Franklin K 
Moore and Simon Ostrach. 1957. iii, 12p. diagrs., 
tabs. (NACA Rept. 1325. Supersedes TN 3886) 



THEORETICAL AND EXPERIMENTAL INVESTIGA- 
TION OF THE SUBSONIC -FLOW FIELDS BENEATH 
SWEPT AND UNSWEPT WINGS WITH TABLES OF 
VORTEX-INDUCED VELOCITIES. William J. 
Alford, Jr. 1957. ii, 43p. diagrs., photo., tabs. 
(NACA Rept. 1327. Supersedes TN 3738) 



THEORETICAL ANALYSIS OF TOTAL-PRESSURE 
LOSS AND AIRFLOW DISTRIBUTION FOR TUBULAR 
TURBOJET COMBUSTORS WITH CONSTANT ANNU- 
LUS AND LINER CROSS -SECTIONAL AREAS. 
Charles C. Graves and Jack S. Grobman. January 
1957. 85p. diagrs., tab. (NACA RM E56I04) 



DESIGN AND TEST OF MDXED-FLOW IMPELLERS. 
Vm - COMPARISON OF EXPERIMENTAL RESULTS 
FOR THREE IMPELLERS WITH SHROUD REDE- 
SIGNED BY RAPID APPROXIMATE METHOD. 
Walter M. Osborn, Kenneth J. Smith, and Joseph T. 
Hamrick. February 1957. 32p. diagrs., photos. 
(NACARM E56L07) 



REFLECTION AND REFRACTION OF ACOUSTIC 
WAVES BY A SHOCK WAVE. (Reflexion et refrac- 
tion d'ondes acoustiques par une onde de choc. ) 
J. Brillouin. July 1957. 42p. diagrs. 
(NACA TM 1409. Translation from Acustica, v. 5, 
no. 3, 1955, p. 149-163) 



(1) AERODYNAMICS 



FLIGHT MEASUREMENTS OF BOUNDARY-LAYER 
TEMPERATURE PROFILES ON A BODY OF REVO- 
LUTION (NACA RM-10) AT MACH NUMBERS FROM 
1.2 TO 3.5. Andrew G. Swanson, James J. Bug 11 a, 
and Leo T. Chauvin. July 1957. 40p. diagrs., 
photos. (NACA TN J 4061) 



STABILITY OF LAMINAR BOUNDARY LAYER NEAR 
A STAGNATION POINT OVER AN IMPERMEABLE 
WALL AND A WALL COOLED BY NORMAL FLUID 
INJECTION. Morris Morduchow, Richard G. Grape, 
and Richard P. Shaw, Polytechnic Institute of 
Brooklyn. August 1957. 56p. diagrs., tabs. 
(NACA TN 4037) 



ANALYSIS OF SHOCK MOTION IN DUCTS DURING 
DISTURBANCES IN DOWNSTREAM PRESSURE. 
Herbert G. Hurrell. September 1957. lip. diagr. 
(NACA TN 4090) 



FLOW-TURNING LOSSES ASSOCIATED WITH ZERO- 
DRAG EXTERNAL-COMPRESSION SUPERSONIC 
INLETS. Rudolph C. Meyer. October 1957. 18p. 
diagrs. (NACA TN 4096) 



HEAT TRANSFER AND RECOVERY TEMPER- 
ATURES ON A SPHERE WITH LAMINAR, TRAN- 
SITIONAL, AND TURBULENT BOUNDARY 
LAYERS AT MACH NUMBERS OF 2.00 AND 4.15. 
Ivan E. Beckwith and James J. Gallagher. 

(NACA TN 4125) 



APPROXIMATE CALCULATION OF THE COMPRES- 
SIBLE TURBULENT BOUNDARY LAYER WITH 
HEAT TRANSFER AND ARBITRARY PRESSURE 
GRADIENT. Eli Reshotko and Maurice Tucker. 
December 1957. 34p. diagrs. (NACA TN 4154) 



DISCHARGE COEFFICIENTS FOR COMBUSTOR- 
LtNER AIR-ENTRY HOLES. H - FLUSH RECTAN- 
GULAR HOLES, STEP LOUVERS, AND SCOOPS. 
Ralph T. Dittrich. April 1958. 56p. diagrs., tab. 
(NACA TN 3924) 



AN EXPERIMENTAL STUDY OF THE TURBULENT 
BOUNDARY LAYER ON A SHOCK-TUBE WALL. 
Paul B. Gooderum. June 1958. 63p. diagrs., 
photos., tab. (NACA TN 4243) 



INTERNAL CHARACTERISTICS AND PERFORM- 
ANCE OF AN AERODYNAMICALLY CONTROLLED, 
VARIABLE-DISCHARGE CONVERGENT NOZZLE. 

Jack G. McArdle. July 1958. 33p. diagrs., photo., 
tabs. (NACA TN 4312) 



COMPRESSD3LE LAMINAR FLOW AND HEAT 
TRANSFER ABOUT A ROTATING ISOTHERMAL 
DISK. Simon Ostrach and Philip R. Thornton. 
August 1958. 18p. diagrs., tab. (NACA TN 4320) 



APPLICATION OF THE METHOD OF COORDINATE 
PERTURBATION TO UNSTEADY DUCT FLOW. 
Seymour C. Himmel, Case Institute of Technology. 
September 1958. (i), I52p. diagrs., tabs. 
(NACA TM 1439) 



SIMILAR SOLUTIONS FOR THE COMPRESSIBLE 
BOUNDARY LAYER ON A YAWED CYLINDER WITH 
TRANSPIRATION COOLING. Ivan E. Beckwith. 
September 1958. 72p. diagrs., tabs. 
(NACA TN 4345) 



TABLES AND GRAPHS OF NORMAL-SHOCK PARAM- 
ETERS AT HYPERSONIC MACH NUMBERS AND 
SELECTED ALTITUDES. Paul W. Huber. September 
1958. 26d. diacrs.. tabs. (NACA TN 4352) 



ANALYTICAL AND EXPERIMENTAL INVESTIGA- 
TION OF TEMPERATURE RECOVERY FACTORS 
FOR FULLY DEVELOPED FLOW OF AIR IN A 
TUBE. R. G. Deissler, W. F. Weiland, and W. H. 
Lowdermilk. September 1958. 35p. diagrs., tab. 
(NACA TN 4376) 



PRELIMINARY HEAT -TRANSFER STUDIES ON TWO 
BODIES OF REVOLUTION AT ANGLE OF ATTACK 
AT A MACH NUMBER OF 3.12. Norman Sands and 
John R. Jack. September 1958. 29p. diagrs., 
photos,, tabs. (NACA TN 4378) 



(1.1.2.1) 
SUBSONIC FLOW 



CALIBRATION OF THE SLOTTED TEST SECTION 
OF THE LANGLEY 8-FOOT TRANSONIC TUNNEL 
AND PRELIMINARY EXPERIMENTAL INVESTIGA- 
TION OF BOUNDARY-REFLECTED DISTURBANCES. 
Virgil S. Ritchie and Alb in O. Pearson. July 1952. 
87p. diagrs., photos. (NACA RM L51K14) 



INVESTIGATION OF CONICAL SUBSONIC DIFFUS- 
ERS FOR RAM-JET ENGINES. John M. Farley and 
Henry J. Welna. March 1954. 40p. diagrs., 
photos., tabs. (NACA RM E53L15) 



PERFORMANCE CHARACTERISTICS OF SEVERAL 
SHORT ANNULAR DIFFUSERS FOR TURBOJET 
ENGINE AFTERBURNERS. William E. Mallett and 
James L. Harp, Jr. May 1954. 31p. diagrs., 
photo . (NACA RM E 54B09) 



LOW-VELOCITY TURNING AS A MEANS OF MINI- 
MIZING BOUNDARY -LAYER ACCUMULATIONS 
RESULTING FROM SECONDARY FLOWS WITHIN 
TURBINE STATORS. Warner L. Stewart and Robert 
Y. Wong. May 1954, 18p. diagrs., photo. 
(NACARME54B16) 



CONTRIBUTIONS ON THE MECHANICS OF 
BOUNDARY-LAYER TRANSITION. G. B. Schubauer 
and P . S. Klebanoff , National Bureau of Standards. 
1956. ii, lip. diagrs. (NACA Rept- 1289. Super- 
sedes TN 3489) 



VISUALIZATION OF ROTOR TIP SECONDARY 
FLOWS WITH BLADE TD? AIR DISCHARGE AND 

SUCTION IN A LOW -SPEED TURBINE . Milton G . 
Kofskey and Hubert W. Allen. August 1956. 28p. 
diagrs., photos. (NACA RM E56E16) 



ON SLENDER -BODY THEORY AT TRANSONIC 
SPEEDS. Keith C Harder and E. B. Klunker. 
1957. ii, 6p. (NACA Rept. 1315. Supersedes 
TN 3815) 



(1) AERODYNAMICS 



THEORETICAL ANALYSIS OF TOTAL -PRESSURE 
LOSS AND AIRFLOW DISTRIBUTION FOR TUBULAR 
TURBOJET COMBUSTORS WITH CONSTANT ANNU- 
LUS AND LINER CROSS-SECTIONAL AREAS. 
Charles C. Graves and Jack S. Grobman. January 
1957. 85p. diagrs., tab. (NACA RM E56I04) 



EFFECT OF*NOSE SHAPE ON SUBSONIC AERO- 
DYNAMIC CHARACTERISTICS OF A BODY OF 
REVOLUTION HAVING A FINENESS RATIO OF 10.94. 
Edward C. Polhamus. August 1957. 29p. diagrs. 
(NACA RM L57F25) 



AN INVESTIGATION OF FLOW IN CIRCULAR AND 
ANNULAR 90° BENDS WITH A TRANSITION IN 
CROSS SECTION. Stafford W. Wilbur. August 
1957. 32p. diagrs., photos., tabs. (NACA TN 3995) 



EXPERIMENTAL INVESTIGATION OF TRANSPIRA- 
TION COOLING FOR A TURBULENT BOUNDARY 
LAY£R IN SUBSONIC FLOW USING AIR AS A 
COOLANT. William E. Brunk. October 1957. 
35p. diagrs. (NACA TN 4091) 



MOMENTUM TRANSFER FOR FLOW OVER A 
FLAT PLATE WITH BLOWING. H. S. Mickley 
and R. S, Davis, Massachusetts Institute of 
Technology. November 1957. 64p. diagrs,, tabs. 
(NACA TN 4017) 



TURBULENCE MEASUREMENTS IN MULTIPLE 
INTERFERING AIR JETS. James C- Laurence and 
JeanM. Benninghoff. December 1957. 37p. 
diagrs., photos. (NACA TN 4029) 



DISCHARGE COEFFICIENTS FOR COMBUSTOR- 
LINER AIR-ENTRY HOLES. II - FLUSH RECTAN- 
GULAR HOLES, STEP LOUVERS, AND SCOOPS. 
Ralph T. Dittrich. April 1958. 56p. diagrs., tab. 
(NACA TN 3924) 



AN APPROXIMATE METHOD FOR DESIGN OR 
ANALYSIS OF TWO-DIMENSIONAL SUBSONIC - 
FLOW PASSAGES. E. Floyd Valentine. April 
1958. 38p. diagrs., photo. (NACA TN 4241) 



LOCAL ISOTROPV IN TURBULENT SHEAR FLOW. 
Stanley Corrsin. Johns Hopkins University. May 
1958. 15p. diagr. (NACA RM 58B11) 



SOME EFFECTS OF VANES AND OF TURBULENCE 
IN TWO-DIMENSIONAL WIDE-ANGLE SUBSONIC 
DIFFUSERS. Carl A. Moore, Jr., and Stephen J. 
Kline, Stanford University. June 1958. iii, 139p. 
diagrs., photos., tabs., film suppl. available on > 
request. (NACA TN 4080) 



ANALYTICAL AND EXPERIMENTAL INVESTIGA- 
TION OF AERODYNAMIC FORCES AND MOMENTS 
ON LOW -ASPECT-RATIO WINGS UNDERGOING 
FLAPPING OSCILLATIONS. Donald S. Woolston, 
Sherman A. Clevenson, and Sumner A. Leadbetter. 
August 1958. 25p. diagrs., tab. (NACA TN 4302) 



SECOND-ORDER SLENDER-BODY THEORY - 
AXISYMMETRIC FLOW. Milton D. Van Dyke. 
September 1958. (i), 46p. (NACA TN 4281) 



EFFECT OF SOME EXTERNAL CROSSWISE STIFF- 
ENERS ON THE HEAT TRANSFER AND PRESSURE 
DISTRIBUTION ON A FLAT PLATE AT MACH NUM- 
BERS OF 0.77, 1.39, AND 1.98. Howard S. Carter. 
September 1958. 21p. diagrs., photo., tab. 
(NACA TN 4333) 



ANALYTICAL AND EXPERIMENTAL INVESTIGA- 
TION OF TEMPERATURE RECOVERY FACTORS 
FOR FULLY DEVELOPED FLOW OF AIR IN A 
TUBE. R. G. Deissler, W. F. Weiland, and W. H. 
Lowdermilk. September 1958. 35p. diagrs., tab. 
(NACA TN 4376) 



(1. 1.2.2) 
MIXED FLOW 



TWO-DIMENSIONAL CHORDWISE LOAD DISTRIBU- 
TIONS AT TRANSONIC SPEEDS. Walter F. Lindsey 
and Richards. Dick. February 1952. 41p. diagrs., 
photos. (NACA RM L51I07) 



CALIBRATION OF THE SLOTTED TEST SECTION 
OF THE LANGLEY 8-FOOT TRANSONIC TUNNEL 
AND PRELIMINARY EXPERIMENTAL INVESTIGA- 
TION OF BOUNDARY-REFLECTED DISTURBANCES. 
Virgil S. Ritchie and Albin O. Pearson. July 1952. 
87p. diagrs., photos. (NACA RM L51K14) 



AIR-FLOW AND POWER CHARACTERISTICS OF 
THE LANGLEY 16-FOOT TRANSONIC TUNNEL 
WITH SLOTTED TEST SECTION. Vernon G. Ward, 
Charles F. White omb, and Merwin D. Pearson. 
July 1952. 50p. diagrs., photos. 
(NACA RM L52E01) 



AN INVESTIGATION OF SOME FACTORS AFFECT- 
ING THE DRAG OF RELATIVELY LARGE NON- 
LIFTING BODIES QF REVOLUTION IN A SLOTTED 
TRANSONIC WIND TUNNEL. Robert E. Pendley 
and Carroll R. Bryan. January 1953. 52p. diagrs., 
photos., tabs. (NACA RM L52H22) 



INVESTIGATION OF THE DRAG OF BLUNT -NOSED 
BODIES OF REVOLUTION IN FREE FLIGHT AT 
MACH NUMBERS FROM 0.6 TO 2.3. Harvey A. 
Wallskog and Roger G. Hart. June 1953. 28p. 
diagrs., photos., tab. (NACA RM L53D14a) 



GENERAL CONSIDERATIONS OF MACH NUMBER 
EFFECTS ON COMPRESSOR-BLADE DESIGN. . 
John F. Klapproth. April 1954. 24p. diagrs., 
photos. (NACA RM E53L23a) 



WING PRESSURE DISTRIBUTIONS AT LOW LIFT 
FOR THE XF-92A DELTA-WING AIRPLANE AT . 
TRANSONIC SPEEDS. Earl R. Keener. October 
1954. 54p. diagrs., photos., tabs. 
(NACA RM H54H06) 



FLOW AND FORCE CHARACTERISTICS OF 
2-PERCENT-THICK AIRFOILS AT TRANSONIC 
SPEEDS. Walter F. Lindsey and Emma Jean 
Landrum. January 1955. 74p. diagrs., photos. 
(NACA RM L54I30) 



(1) AERODYNAMICS 



SOME STUDIES OF AXISYMMETRIC FREE JETS 
EXHAUSTING FROM SONIC AND SUPERSONIC 
NOZZLES INTO STILL AIR AND INTO SUPERSONIC 
STREAMS. Eugene S. Love and Carl E. Grlgsby. 
May 1955. ii, i7Sp. diagrs., photos., tabs. 
(NACA RM L54L31) 



A STUDY OF LOCAL-PRESSURE FLUCTUATIONS 
RELATIVE TO STATIC -PRESSURE DISTRIBUTIONS 
OF TWO-DIMENSIONAL AIRFOILS AT HIGH SUB- 
SONIC MACH NUMBERS. Charles F. Coe. 
December 1955. 66p. diagrs., photos. 
{NACARM A55J11) 



INFLUENCE OF THE BODY FLOW FIELD ON THE 
ZERO-LIFT WAVE DRAG OF WING-BODY COMBI- 
NATIONS MODIFIED IN ACCORDANCE WITH THE 
TRANSONIC AREA RULE. William A. Page. 
February 1956. 26p. diagrs. (NACA RM A55K10) 



INVESTIGATION OF UNSTEADY FLOW PAST FOUR 
NACA 6-PERCENT-THICK AIRFOIL SECTIONS. 
Charles L. Ladson and Walter F. Lindsey. July 
1956. 17p. diagrs. (NACA RM L56E14) 



ON SLENDER -BODY THEORY AT TRANSONIC 
SPEEDS. Keith C Harder and E. B. Klunker. 
1957. ii, 6p. (NACARept. 1315. Supersedes 
TN 3815) 



THREE-DIMENSIONAL TRANSONIC FLOW THEORY 
APPLIED TO SLENDER WINGS AND BODIES. 
Max. A. Heaslet and John R. Spreiter. 1957. 
iii, 29p. diagrs. (NACA Rept. 1318. Supersedes 
TN 3717) 



THEORETICAL ANALYSIS OF TOTAL -PRESSURE 
LOSS AND AIRFLOW DISTRIBUTION FOR TUBULAR 
TURBOJET COMBUSTORS WITH CONSTANT ANNU- 
LUS AND LINER CROSS -SECTIONAL AREAS. 
Charles C. Graves and Jack S. Grobman. January 
1957. 85p. diagrs., tab. (NACA RM E56I04) 



A REEXAMINATION OF THE USE OF SIMPLE 
CONCEPTS FOR PREDICTING THE SHAPE AND 
LOCATION OF DETACHED SHOCK WAVES. 
Eugene S. Love. December 1957. 53p. diagrs. 
(NACA TN 4170) 



THEORETICAL PRESSURE DISTRIBUTIONS FOR 
SEVERAL RELATED NONLIFTING AIRFOILS AT 
HIGH SUBSONIC SPEEDS. John R. Spreiter, 
Alberta Y. Alksne, andB. Jeanne Hyett. January 
1958. (i), 52p. diagrs., tab. (NACA TN 4148) 



COMPILATION OF INFORMATION ON THE TRAN- 
SONIC ATTACHMENT OF FLOWS AT THE LEAD- 
ING EDGES OF AIRFOILS. Walter F. Lindsey and 
Emma Jean Landrum. February 1958. 63p. 
diagrs., photos., tabs. (NACA TN 4204) 



THE INTERACTION OF A REFLECTED SHOCK 
WAVE WITH THE BOUNDARY LAYER IN A SHOCK 
TUBE. Herman Mark, Cornell University. March 
1958. ii, 128p. diagrs., photos., tabs. 
(NACA TM 1418) 



EXPERIMENTAL STUDY OF THE EQUIVALENCE 
OF TRANSONIC FLOW ABOUT SLENDER CONE- 
CYLINDERS OF CIRCULAR AND ELLD?TIC CROSS 
SECTION. William A. Page. April 1958. 45p. 
diagrs., photos., tab. (NACA TN 4233) 



MEASUREMENTS OF THE EFFECTS OF WALL 
OUTFLOW AND POROSITY ON WAVE ATTENUATION 
IN A TRANSONIC WIND TUNNEL WITH PERFO- 
RATED WALLS. Joseph M. Spiegel, Phillips J. 
Tunnell, and Warren S. Wilson. August 1958. 27p. 
diagrs. (NACA TN 4360) 



THEORY AND EXPERIMENTS ON SUPERSONIC AIR- 
TO-AIR EJECTORS. (Theorie et experimentation des 
ejecteurs supersoniques ah -air .) J. Fabri and 
J. Paulon. September 1958. 30p. diagrs. . (NACA 
TM 1410. Translation of Office National d'Etudes et 
de Recherches Aeronautiques. Note Technique 
no. 36, 1956) 



(1.1.2.3) 

SUPERSONIC FLOW 



SUPERSONIC-TUNNEL TESTS OF TWO SUPER- 
SONIC AIRPLANE MODEL CONFIGURATIONS. 
Macon C. Ellis, Jr., Lowell E. Hasel, and Carl E. 
Grigsby. December 31, 1947. 49p. diagrs., 
photos., tab. (NACA RM L7J15) 



EXPERIMENTAL PRESSURE DISTRIBUTION ON AN 
ASYMMETRICAL NONCONICAL BODY AT MACH 
NUMBER 1.90. DeMarquis D. Wyatt. February 24, 
1949. 58p. diasrs.. photos., tabs. 
(NACA RM E9B03) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR-ARC SECTIONS AND 40<> SWEEPBACK. 
A PRESSURE-DISTRIBUTION STUDY OF THE AERO- 
DYNAMIC CHARACTERISTICS OF THE WING AT 
MACH NUMBER 1.59. Morton Cooper and M, Leroy 
Spearman. May 23, 1950. 52p. diagrs., photos., 
tabs. (NACA RM L50C24) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR-ARC SECTION AND 40° SWEEPBACK. 
A PRESSURE-DISTRIBUTION STUDY OF THE AERO- 
DYNAMIC CHARACTERISTICS OF THE WING AT 
MACH NUMBER 1.40. Norman F. Smith, Julian H. 
Kainer, and Robert A. Webster. April 20, 1951. 
48p. diagrs., photos., tabs. (NACA RM L51C06) 



UESIGN AND PERFORMANCE OF AN EXPERIMEN- 
TAL AXIAL-DISCHARGE MDCED-FLOW COM- 
PRESSOR. IH - OVER-ALL PERFORMANCE OF 
IMPELLER AND SUPERSONIC -DIFFUSER COMBI- 
NATION, Ward W. Wilcox and William H. Robbins. 
April 30, 1951. 26p. diagrs., photo. 
(NACA RM E51A02) 



INVESTIGATION OF OFF-DESIGN PERFORMANCE 
OF SdOCK-IN-ROTOR TYPE SUPERSONIC 
BLADING. Robert C. Graham, John F. Klapproth, 
and Frank J. Barina. May 7, 1951. 25 p. diagrs., 
photos. (NACA RM E51C22) 



EXPERIMENTAL INVESTIGATION OF A 16-INCH 
IMPULSE-TYPE SUPERSONIC -COMPRESSOR 
ROTOR. Guy N. Ullman, Melvin J. Hartmann, and 
Edward R. Tysl. October 1951. 29p. diagrs., 
photos. (NACA RM E51G19) 



8 



(1) AERODYNAMICS 



INVESTIGATION OF A 24-INCH SHOCK-IN-ROTOR 
TYPE SUPERSONIC COMPRESSOR DESIGNED FOR 
SIMPLE RADIAL EQUILIBRIUM BEHIND NORMAL 
SHOCK. Harold Lown and Melvin J. Hartmann. 
December 1951. 25p. diagrs., photo. 
(NACA RM E51H08) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR-ARC SECTIONS AND 40° SWEEPBACK. 
ESTIMATED DOWNWASH ANGLES DERIVED FROM 
PRESSURE MEASUREMENTS ON THE TAIL AT 
MACH NUMBERS OF 1.40 AND 1.59. Frederick C. 
Grant and John P. Gapcynski. March 1952. 27p. 
diagrs., photos., tabs. (NACA RM L5JL17) 



AN INVESTIGATION AT MACH NUMBERS OF 1.62 
AND 1.93 OF THE LIFT EFFECTIVENESS AND 
INTEGRATED DOWNWASH CHARACTERISTICS OF 
SEVERAL IN-LINE MISSILE CONFIGURATIONS 
HAVING EQUAL-SPAN WINGS AND TAILS. Carl E. 
Grigsby. April 1952. 75p. diagrs., tabs. 
(NACA RM L52A02) 



AERODYNAMICS OF SLENDER BODIES AT MACH 
NUMBER OF '3.12 AND REYNOLDS NUMBERS 
FROM 2 x 106 TO 15 x 106. II - AERODYNAMIC 
LOAD DISTRIBUTIONS OF SERIES OF FIVE BODIES 
HAVING CONICAL NOSES AND CYLINDRICAL 
AFTERBODIES. John R. Jack and Lawrence I. 
Gould. May 1952. 28p. diagrs., photos., tabs. 
(NACA RM E52C10) 



CALIBRATION OF THE SLOTTED TEST SECTION 
OF THE LANGLEY 8-FOOT TRANSONIC TUNNEL 
AND PRELIMINARY EXPERIMENTAL INVESTIGA- 
TION OF BOUNDARY-REFLECTED DISTURBANCES. 
Virgil S. Ritchie and Albin O. Pearson. July 1952. 
87p. diagrs., photos. (NACA RM L51K14) 



AIR-FLOW AND POWER CHARACTERISTICS OF 
THE LANGLEY 16-FOOT TRANSONIC TUNNEL 
WITH SLOTTED TEST SECTION. Vernon G. Ward, 
Charles F. Whitcomb, and Merwin D. Pearson. 
July 1952. 50p. diagrs., photos. 
(NACA RM L52E01) 



FORCES AND MOMENTS ON POINTED AND BLUNT - 
NOSED BODIES OF REVOLUTION AT MACH NUM- 
BERS FROM 2.75 TO 5.00. David H. Dennis and 
Bernard E. Cunningham. August 1952. 47p. 
diagrs., photo., tabs. (NACA RM A52E22) 



INVESTIGATION OF INTERFERENCE LIFT, DRAG, 
AND PITCHING MOMENT OF A SERIES OF REC- 
TANGULAR WING AND BODY COMBINATIONS AT 
MACH NUMBERS OF 1.62, 1.93, AND 2.41. Donald 
E. Coletti. August 1952. 74p. diagrs., tabs. 
(NACARML52E26) 



A PRESSURE -DISTRIBUTION INVESTIGATION OF A 
FINENESS-RATIO-12.2 PARABOLIC BODY OF REV- 
OLUTION (NACA RM-10) AT M = 1.59 AND 
ANGLES OF ATTACK UP TO 36°. Morton Cooper, 
John P. Gapcynski, and Lowell E. Hasel. October 
1952. 89p. diagrs., photos., tabs. 
(NACA RM L52G14a) 



SOME OBSERVATIONS OF FLOW AT THE THROAT 
OF A TWO-DIMENSIONAL DIFFUSER AT THE 
MACH NUMBER OF 3.85. James F. Connors and 
Richard R. Woolleit. November 1952. 13p. photos., 
diagrs. (NACA RM E52I04) 



PERFORMANCE OF A SWEPT LEADING EDGE 
ROTOR OF THE SUPERSONIC TYPE WITH MIXED 
FLOW. Arthur W. Goldstein and Ralph L. Schacht. 
January 1953, 34p. diagrs., photo., tab. 
(NACARM E52K03) 



SOME EFFECTS OF A SONIC JET EXHAUST ON 
THE LOADING OVER A YAWED FIN AT A MACH 
NUMBER OF 3.03. John E. Hatch, Jr., and William 
M. Savelle. January 1953. 12p. diagrs., photo. 
(NACA RM L52L02a) 



LOAD DISTRIBUTIONS ASSOCIATED WITH CON- 
TROLS AT SUPERSONTC SPEEDS. K. R. Czamecki 
and Douglas R. Lord. May 1953. 21p. photo., 
diagrs. (NACA RM L53D15*) 



INVESTIGATION OF 16-INCH IMPULSE-TYPE 
SUPERSONIC COMPRESSOR WITH ROTOR TURN- 
ING PAST AXIAL DIRECTION. John J. Jacklitch, 
Jr., and Melvin J. Hartmann. July 1953. ?9p. 
dinars., photos. (NACA RM E53D13) 



INVESTIGATION OF A SUPERSONIC-COMPRESSOR 
ROTOR WITH TURNING TO AXIAL DIRECTION. I - 
ROTOR DESIGN AND PERFORMANCE. Edward R. 
Tysl, John F. Klapproth, and Melvin J. Hartmann. 
August 1953. 36p. diagrs., photos. 
(NACA RM E53F23) 



UTILIZATION OF EXTERNAL-COMPRESSION DIF- 
FUSION PRINCIPLE IN DESIGN OF SHOCK-IN- 
ROTOR SUPERSONIC COMPRESSOR BLADING. 
John W. R. Creagh and John F. Klapproth. 
September 1953. 37p. diagrs., photos., tab. 
(NACA RM E53F18) 



THEORETICAL CALCULATIONS OF THE STABILI- 
TY DERIVATIVES AT SUPERSONIC SPEEDS FOR A 
HIGH-SPEED AIRPLANE CONFIGURATION. 
Kenneth Margolis and Percy J. Bobbitt. October 
1953. 59p. diagrs., tab. (NACA RM L53G17) 



INVESTIGATION AT MACH NUMBERS OF 1 .62, 1 .93. 
AND 2.41 OF THE EFFECT OF OSCILLATION 
AMPLITUDE ON THE DAMPING IN PITCH OF 
DELTA -WING -BODY COMBINATIONS- Arthur 
Henderson, Jr. October 1953. 28p. diagrs.. 
photos. (NACA RM L53H25) 



THE EFFECT OF NOSE RADIUS AND SHAPE ON 
THE AERODYNAMIC CHARACTERISTICS OF A 
FUSELAGE AND A WING -FUSELAGE COMBINATION 
AT ANGLES OF ATTACK. John P. Gapcynski and 
A. Warner Robins. October 1953. 23p. diagrs. 
(NACA RM L53l23a) 



PERFORMANCE OF A SUPERSONIC MIXED-FLOW 
ROTOR WITH A SWEPT LEADING EDGE AND 0.52 
INLET RADIUS RATIO. Arthur W. Goldstein and 
Ralph L. Schacht. November 1953. 34p. diagrs., 
photos., tab. (NACARM E53H27) 



AN INVESTIGATION AT MACH NUMBER 2.40 OF 
FLAP-TYPE CONTROLS EQUDPPED WITH OVER- 
HANG NOSE BALANCES. James N. Mueller. 
November 1953. 95p. diagrs., photos., tab. 
(NACA RM L53I21) 



(1) AERODYNAMICS 



STATIC LATERAL STABILITY CHARACTERISTICS 
OF A 1, 16-SCALK MODEL OF THE DOUGLAS 
D-558-II RESEARCH AIRPLANE AT MACH NUM- 
BERS OF 1.61 AND 2.01. Frederick C. Grant and 
Ross B. Robinson. November 1953. 39p. diagrs., 
photo., tabs. (NACA RM L53I29a) 



AN EXPERIMENTAL INVESTIGATION OF THE 
TRANSONIC-FLOW-GENERATION AND SHOCK- 
WAVE-REFLECTION CHARACTERISTICS OF A 
TWO-DIMENSIONAL WR4D TUNNEL WITH 24- 
PERCENT-OPEN, DEEP, MULTISLOTTED WALLS. 
Thomas B. Sellers, Don D. Davis, and George M. 
Stokes. December 1953. 37p. diagrs., photos. 
(NACA RM L53J28) 



INVESTIGATION OF A SUPERSONIC-COMPRESSOR 
ROTOR WITH TURNING TO AXIAL DIRECTION. 
II - ROTOR COMPONENT OFF-DESIGN AND STAGE 
PERFORMANCE. Melvin J. Hartmann and Edward 
R. Tysl. March 1954. 3lp. diagrs., photos. 
(NACA RM E53L24) 



AERODYNAMIC CHARACTERISTICS OF A FULL- 
SPAN TRAILING-EDGE CONTROL ON A 60° DELTA 
WING WITH AND WITHOUT A SPOILER AT MACH 
NUMBER 1.61. Douglas R. Lord and K. R. 
Czarneckl. March 1954. 49p. diagrs., photos., 
tab. (NACA RM L53L17) 



AERODYNAMIC CHARACTERISTICS OF TWO FLAT- 
BOTTOMED BODIES AT MACK NUMBER OF 3.12. 
John R. Jack and Barry Moskowitz. April 1954. 
9p. diagrs. (NACA RM E53Lllb) 



AN ANALYSIS OF PRESSURE STUDIES AND EX- 
PERIMENTAL AND THEORETICAL DOWNWASH 
AND SIDEWASH BEHIND FIVE POINTED-TIP WINGS 
AT SUPERSONIC SPEEDS. William B. Boatright. 
April 1954. ii, H9p. diagrs., photos. 
(NACA RM L54B10) 



OPTIMUM LIFTING BODIES AT HIGH SUPERSONIC 
AIRSPEEDS. Meyer M. Resnikoff. May 1954. 
22p. diagrs., photo. (NACA RM A54B15) 



LOW-VELOCITY TURNING AS A MEANS OF MINI- 
MIZING BOUNDARY-LAYER ACCUMULATIONS 
RESULTING FROM SECONDARY FLOWS WITHIN 
TURBINE STATORS. Warner L. Stewart and Robert 
Y. Wong. May 1954. 18p. diagrs., photo. 
(NACARME54B16) 



JET EFFECTS ON PRESSURE LOADING OF ALL- 
MOVABLE HORIZONTAL STABILIZER. Alfred S. 
Valerino. June 1954. 27p. diagrs., photo., tab. 
(NACA RM E54C24) 



PERFORMANCE OF A SUPERSONIC ROTOR HAVING 
HIGH MASS FLOW. Ralph L. Schacht, Arthur W. 
Goldstein, and Harvey E. Neumann. July 1954. 
34p. diagrs., photo., tab. (NACA RM E54D22) 



AERODYNAMIC CHARACTERISTICS OF SEVERAL 
TIP CONTROLS ON A 60° DELTA WING AT A MACH 
NUMBER OF 1.61. Douglas R. Lord and K. R. 
Czarnecki. August 1954. 44p. diagrs., photos., 
tabs. (NACA RM L54E25) 



A METHOD FOR INCREASING THE EFFECTIVE- 
NESS OF STABILIZING SURFACES AT HIGH SUPER- 
SONIC MACH NUMBERS. Charles H. Mc-Lellan. 
August 1954. 14p. diagrs. {NACA RM L54F21) 



INVESTIGATION OF SUPERSONIC-COMPRESSOR 
ROTORS DESIGNED WITH EXTERNAL COMPRES- 
SION. Lawrence J. Jahnsen and Melvin J. 
Hartmann. September 1954. 41p. diagrs., photos. 
(NACA RM E54G27a) 



INVESTIGATION OF THE AERODYNAMIC CHARAC- 
TERISTICS AT HIGH SUPERSONIC MACH NUMBERS 
OF A FAMILY OF DELTA WINGS HAVING DOUBLE- 
WEDGE SECTIONS WITH THE MAXIMUM THICK- 
NESS AT 0.18 CHORD. Mitchel H. Bertram and 
William D. McCauley. October 1954. 54p. diagrs., 
photos., tabs. (NACA RM L54G28) 



INVESTIGATION AT SUPERSONIC SPEEDS OF THE 
EFFECT OF JET MACH NUMBER AND DIVER- 
GENCE ANGLE OF THE NOZZLE UPON THE PRES- 
SURE OF THE BASE ANNULUS OF A BODY OF 
REVOLUTION. August F. Bromm, Jr., and Robert 
M. O'Donnell. December 1954. 24p. diagrs., 
photos. (NACA RM L54I16) 



DESIGN AND PERFORMANCE OF A 1400-FOOT-PER- 
SECOND-TIP-SPEED SUPERSONIC COMPRESSOR 
ROTOR. John F. Klapproth, John J. Jacklltch, Jr., 
and Edward R. Tysl. April 1955. 48p. diagrs., 
photo., tab. (NACA RM E55A27) 



SOME STUDIES OF AXISYMMETRIC FREE JETS 
EXHAUSTING FROM SONIC AND SUPERSONIC 
NOZZLES INTO STILL AIR AND INTO SUPERSONIC 
STREAMS. EugeneS. Love and Carl E. Grlgsby. 
May 1955. 11, 178p. diagrs., photos., tabs. 
(NACA RM L54L31) 



INVESTIGATION OF INTERFERENCE LIFT, DRAG, 
AND PITCHING MOMENT OF A SERIES OF TRI- 
ANGULAR WING AND BODY COMBINATIONS AT A 
MACH NUMBER OF 1.62. Donald E. Coletti. May 
1955, 49p. diagrs., photo., tabs. 
(NACA RM L55B25) 



INVESTIGATION OF THE EFFECTS OF BODY 
INDENTATION AND OF WING-PLAN-FORM 
MODIFICATION ON THE LONGITUDINAL CHARAC- 
TERISTICS OF A 60° SWEPT -WING-BODY COMBI- 
NATION AT MACH NUMBERS OF 1.41, 1.61, AND 
2.01. John R. Sevier, Jr. July 1955. 37p. diagrs., 
tab. (NACARM L55E17) 



A VARIABLE-GEOMETRY AXISYMMETRIC SUPER- 
SONIC INLET WITH TELESCOPING CENTERBODY. 
James F. Connors and Rudolph C. Meyer. 
September 1955. 27p. diagrs., photos., tabs. 
(NACA RM E55F30) 



THE EFFECT OF FLUID INJECTION ON THE COM- 
PRESSIBLE TURBULENT BOUNDARY LAYER - 
PRELIMINARY TESTS ON TRANSPIRATION COOL- 
ING OF A FLAT PLATE AT M = 2.7 WITH AIR AS 
THE INJECTED GAS. Morris W. Rubesin, 
Constantine C. Pappas, and Arthur F. Okuno. 
December 1955, 37p. diagrs. (NACA RM A55I19) 



10 



(1) AERODYNAMICS 



INVESTIGATION OF INTERFERENCE LIFT, DRAG, 
AND PITCHING MOMENT OF A SERIES OF 
TRIANGULAR-WING AND BODY COMBINATIONS 
AT A MACH NUMBER OF 1.94. Donald E. Coletti. 
December 1955. 52p. diagrs., photo., tabs. 
(NACA RM L55I14) 



A METHOD FOR THE DESIGN OF POROUS -WALL 
WIND TUNNELS. George M. Stokes. January 
1956. 5 Op. diagrs., photo., tabs. 
(NACA RM L55J13a) 



INrTIAL INCLINATION OF THE MIXING BOUNDARY 
SEPARATING AN EXHAUSTING SUPERSONIC JET 
FROM A SUPERSONIC AMBIENT STREAM. 
Eugenes. Love. January 1956. 30p. diagrs. 
(NACA RM L55J14) 



THE INFLUENCE OF SURFACE INJECTION ON 
HEAT -TRANSFER AND SKIN FRICTION ASSOCI- 
ATED WITH THE HIGH-SPEED TURBULENT 
BOUNDARY LAYER. Morris W. Rubesln. 
February 1956. 16p. diagrs. (NACA RM A55L13) 



CRITERIA FOR INITIAL FLOW REVERSAL IN 
SYMMETRICAL TWIN-INTAKE AIR-INDUCTION 
SYSTEMS OPERATING AT SUPERSONIC SPEEDS. 
Andrew Beke. February 1956. 17p. diagrs. 
(NACA RM E55L02a) 



AERODYNAMIC LOADINGS ASSOCIATED WITH 
SWEPT AND UNSWEPT SPOILERS ON A FLAT 
PLATE AT MACH NUMBERS OF 1.81 AND 2.01. 
Douglas R. Lord and K. R Czarnecki. March 1956. 
174p. diagrs., photos., tabs. (NACA RM L55L12) 



EFFECT OF MACH NUMBER ON BOUNDARY- 
LAYER TRANSITION IN THE PRESENCE OF PRES- 
SURE RISE AND SURFACE ROUGHNESS ON AN 
OGIVE -CYLINDER BODY WITH COLD WALL 
CONDITIONS. Robert J. Carros. April 1956. 
30p. diagrs., photos. (NACA RM A56B15) 



EXPERIMENTAL INVESTIGATION OF INTERFER- 
ENCE EFFECTS OF LATERAL -SUPPORT STRUTS 
ON AFTERBODY PRESSURES AT MACH 1.9. John 
L. Klann and Ronald G. Huff. May 1956. 13p. 
diagrs., tab. (NACA RM E56C16) 



EFFECT OF WING CAMBER AND TWIST AT MACH 
NUMBERS FROM 1.4 TO 2.1 ON THE LIFT, DRAG, 
AND LONGITUDINAL STABILITY OF A ROCKET- 
POWERED MODEL HAVING A 52.5° SWEPTBACK 
WING OF ASPECT RATIO 3 AND INLINE TAIL SUR- 
FACES. Warren Gillespie, Jr. May 1956. 29p. 
diagrs., photos., tabs. (NACA RM L56C16) 



THE EFFECT OF FLUID INJECTION ON THE 
COMPRESSIBLE TURBULENT BOUNDARY LAYER 
- THE EFFECT ON SKIN FRICTION OF AIR 
INJECTED INTO THE BOUNDARY LAYER OF A 
CONE AT M = 2.7. Thorval Tendeland and Arthur 
F. Okuno. June 1956. 23p. diagrs. 
(NACA RM A56D05) 



WIND-TUNNEL INVESTIGATION OF THE DAMPING 
IN ROLL OF THE DOUGLAS D-558-B. RESEARCH 
AIRPLANE AND ITS COMPONENTS AT SUPERSONIC 
SPEEDS. Russell W. McDearmon. September 1956. 
36p. diagrs., photos. (NACA RM L56F07) 



WIND-TUNNEL INVESTIGATION OF DAMPING IN 
ROLL AT SUPERSONIC SPEEDS OF TRIANGULAR 
WINGS AT ANGLES OF ATTACK. Russell W. 
McDearmon and Robert A. Jones. September 1956. 
32p diagrs., photos., tab. (NACA RM L56F13a) 



BOUNDARIES OF SUPERSONIC AXBYMMETRIC 
FREE JETS. EugeneS. Love, Mildred J. Woodling, 
and Louise P. Lee. October 1956. 98p. diagrs. 
(NACA RM I R6G18) 



LINEARIZED LIFTING -SURFACE AND LIFTING- 
LINE EVALUATIONS OF SIDEWASH BEHIND ROLL- 
ING TRIANGULAR WINGS AT SUPERSONIC SfucDS. 
Percy J. Bobbitt. 1957. 11, 19p. diagrs., photo. 
(NACA Rept. 1301- Supersedes TN 3609^ 



BODIES OF REVOLUTION HAVING MINIMUM DRAG 
AT HIGH SUPERSONIC AIRSPEEDS. A.J. Eggers, 
Jr., Meyer M. Resnlkoff, and David H. Dennis. 
1957. il, 12p. diagrs., photos. (NACA Rept. 1306. 
Supersedes TN 3666) 



AN INVESTIGATION OF FOUR WINGS OF SQUARE 
PLAN FORM AT A MACH NUMBER OF 6.9 IN THE 
LANGLEY 11 -INCH HYPERSONIC TUNNEL. 
Charles H. McLeUan, MitchelH. Bertram, and 
John A. Moore. 1957. ii, 18p. diagrs., photos. 
(NACA Rept. 1310. Supersedes RM L51D17) 



SOME EFFECTS OF BLUNTNESS ON BOUNDARY* 
LAYER TRANSITION AND HEAT TRANSFER AT 
SUPERSONIC SPEEDS. W. E. Moeckel. 1957., 
ii, 14p. diagrs. (NACA Rept. 1312. Supersedes 
TN 3653) 



EXPLORATORY INVESTIGATION OF BOUNDARY- 
LAYER TRANSITION ON A HOLLOW CYLINDER AT 
A MACH NUMBER OF 6.9. Mitchel H. Bertram. 
1957. ii, 27p. diagrs., photos. (NACA Rept. 1313. 
Supersedes TN 3546) 



ON SLENDER-BODY THEORY AT TRANSONIC 
SPEEDS. Keith C. Harder and E. B. Klunker. 
1957. ii, 6p. (NACA Rept. 1315. Supersedeb 
TN 3815) 



AN EVALUATION OF FOUR EXPERIMENTAL 
METHODS FOR MEASURING MEAN PROPERTIES 
OF A SUPERSONIC TURBULENT BOUNDARY 
LAYER. George J. Nothwang. 1957. ii, lip. 
diagrs., photos. (NACA Rept. 1320. Supersedes 
TN 3721) 



A SECOND-ORDER SHOCK- EXPANSION METHOD 
APPLICABLE TO BODIES OF REVOLUTION NEAR 
ZERO LIFT. Clarence A. Syvertson and David H. 
Dennis. 1957. ii, 20p. diagrs., tabs. 
(NACA Rept. 1328. Supersedes TN 3527) 



MINIMUM WAVE DRAG FOR ARBITRARY ARRANGE- 
MENTS OF WINGS AND BODIES. Robert T. Jones. 
1957. ii, 6p. diagrs., photo. (NACA Rept. 1335. 
Supersedes TN 3530) 



(1) AERODYNAMICS 



11 



INVESTIGATION OF DOWNWASH, SIDEWASH, AND 
MACU NUMBER DISTRIBUTION BEHIND A RECTAN- 
GULAR WING AT A MACH NUMBER OF 2.41. 
David Adamson and William B. Boatrlght. 1967. 
11, 57p. diagrs., photos., tab. (NACA Rept. 1340. 
Supersedes RM L50G12) 



THE MINIMIZATION OF WAVE DRAG FOR WINGS 
AND BODIES WITH GIVEN BASE AREA OR 
VOLUME. Max. A. Heaslet. July 1957. 27p. 

(NACA TN 3289) 



EXPERIMENTAL INVESTIGATION OF ATTENUA- 
TION OF STRONG SHOCK WAVES IN A SHOCK 
TUBE WITH HYDROGEN AND HELIUM AS DRIVER 
GASES. Jim J. Jones. July 1957. 24p. diagrs., 
"hoio. (NACA TN 4072) 



EQUATIONS, TABLES, AND FIGURES FOR USE IN 
THE ANALYSIS OF HELIUM FLOW AT SUPERSONIC 
AND HYPERSONIC SPEEDS. James N. Mueller. 
September 1957. 178p. diagrs., tab. (NACA TN 4063) 



ANALYSIS OF SHOCK MOTION IN DUCTS DURING 
DISTURBANCES IN DOWNSTREAM PRESSURE. 
Herbert G. Hurrell. September 1957. Up. diagr. 
(NACA TN 4090) 



HEAT TRANSFER AND BOUNDARY-LAYER TRAN- 
SITION ON TWO BLUNT BODIES AT MACH NUMBER 
3.12. N. S- Dlaconis, Richard J. Wisnicwski, and 
John R. Jack. October 1957. 31p. diagrs., photo. 
(NACA TN 4099) 



STUDY OF PRESSURE DISTRIBUTIONS ON SIMPLE 
SHARP-NOSED MODELS AT MACH NUMBERS FROM 
16 TO 18 IN HELIUM FLOW. Wayne D. Erickson. 
October 1957. 42p. diagrs., photos. 
(NACA TN 4113) 



A RAPID METHOD FOR PREDICTING ATTACHED- 
SHOCK SHAPE. Eugene S. Love and Ronald H. 
Long. October 1957. 34p. diagrs., tab. 
(NACA TN 4167) 



HEAT TRANSFER AND RECOVERY TEMPER- 
ATURES ON A SPHERE WITH LAMINAR, TRAN- 
SITIONAL, AND TURBULENT BOUNDARY 
LAYERS AT MACH NUMBERS OF 2.00 AND 4.15. 
Ivan E. Beckwith and James J. Gallagher. 
December 1957. 59p. diagrs., photos. 
(NACA TN 4125) 



EFFECTS OF LEADING-EDGE BLUNTING ON THE 
LOCAL HEAT TRANSFER AND PRESSURE DISTRI- 
BUTIONS OVER FLAT PLATES IN SUPERSONIC 
FLOW. Marcus O. Creager. December 1957. 
54p. diagrs., tabs. (NACA TN 4142) 



LAMINAR BOUNDARY LAYER WITH HEAT TRANS- 
FER ON A CONE AT ANGLE OF ATTACK IN A 
SUPERSONIC STREAM. Eli Reshotko. December 
1957. (i), 64p. diagrs., tabs. (NACA TN 4152) 



A REEXAMINATION OF THE USE OF SIMPLE 
CONCEPTS FOR PREDICTING THE SHAPE AND 
LOCATION OF DETACHED SHOCK WAVES. 
Eugene S. Love. December 1957. 53p. diagrs. 
(NACA TN 4170) 



EFFECT OF ANGLE OF ATTACK AND THICKNESS 
ON AERODYNAMIC COEFFICIENTS OF A RIGID 
WING OSCILLATING AT VERY LOW FREQUENCIES 
IN TWO-DIMENSIONAL SUPERSONIC FLOW. 
Franks. Maivestuto, Jr., andJuiiaM. Goodwin. 
January 1958. 65p. diagrs. (NACA TN 4069) 



THEORETICAL CALCULATIONS OF SUPERSONIC 
WAVE DRAG AT ZERO LIFT FOR A PARTICULAR 
STORE ARRANGEMENT. Kenneth Margolis, 
Frank S. Maivestuto, Jr., and Peter J. Maxie, Jr. 
January 1958. 37p. diagrs., tab. (NACA TN 4120) 



SHAPE OF INITIAL PORTION OF BOUNDARY OF 
SUPERSONIC AXISYMMETRIC FREE JETS AT 
LARGE JET PRESSURE RATIOS. Eugene S. Love 
and Louise P. Lee. January 1958. 29p. diagrs. 
(NACA TN 4195) 



TURBULENT BOUNDARY LAYER ON A YAWED 
CONE IN A SUPERSONIC STREAM. Willis H. 
Braun. January 1958. 39p. diagrs. 
(NACA TN 4208) 



BOUNDARY-LAYER DISPLACEMENT EFFECTS IN 
AIR AT MACH NUMBERS OF 6.8 AND 9.6. 
Mitchel H. Bertram. February 1958. 61p. diagrs., 
photos. (NACA TN 4133) 



INVESTIGATION OF SPOILERS AT A MACH NUM- 
BER OF 1.93 TO DETERMINE THE EFFECTS OF 
HEIGHT AND CHORDWISE LOCATION ON THE 
SECTION AERODYNAMIC CHARACTERISTICS OF A 
TWO-DIMENSIONAL WING. James N. Mueller. 
February 1958. 52p. diagrs., photos. 
(NACA TN 4180. Supersedes RM L52L31) 



RECOVERY TEMPERATURES AND HEAT TRANS- 
FER NEAR TWO-DIMENSIONAL ROUGHNESS 
ELEMENTS AT MACH 3.1. Paul F. Brinich. 
February 1958. 20p. diagrs. (NACA TN 4213) 



BOUNDARY-LAYER TRANSITION ON AN OPEN- 
NOSE CONE AT MACH 3.1. Paul F. Brinich. 
February 1958. lip. diagrs. (NACA TN 4214) 



DRAG MINIMIZATION FOR WINGS IN SUPERSONIC 
FLOW, WITH VARIOUS CONSTRAINTS. Max. A. 
Heaslet and Franklyn B. Fuller. February 1958. 
30p. (NACA TN 4227) 



APPROXIMATIONS FOR THE THERMODYNAMIC 
AND TRANSPORT PROPERTIES OF HIGH- 
TEMPERATURE AIR. C Frederick Hansen. 
March 1958. 67p. diagrs., tabs. (NACA TN 4150) 



PRANDTL-MEYER EXPANSION OF CHEMICALLY 
REACTING GASES IN LOCAL CHEMICAL AND 
THERMODYNAMIC EQUILIBRIUM. Steve P. Heims. 
March 1958. 17p. diagrs. (NACA TN 4230) 



EXTREME SPEEDS AND THERMODYNAMIC 
STATES IN SUPERSONIC FLIGHT. (Extreme 
Geschwindigkeiten und thermische Zustande beim 
Uberschallflug.) Klaus Oswatitsch. April 1958. 
39p. diagrs., tabs. (NACA TM 1434. Translation 
from Zeitschrift fur Flugwissenschaften, v. 4, 
no. 3/4, 1956, p. 95-108) 



12 



(1) AERODYNAMICS 



OBSERVATIONS OF TURBULENT-BURST GEOM- 
ETRY AND GROWTH IN SUPERSONIC FLOW. 

Carlton S. James. April 1958. (i), 85p. diagrs., 
photos., tab. (NACA TN 4235) 



EFFECTS OF MACH NUMBER AND WALL- 
TEMPERATURE RATIO ON TURBULENT HEAT 
TRANSFER AT MACH NUMBERS FROM 3 TO 5. 
Thorval Tendeland. April 1958. 46p. diagrs. 
(NACA TN 4236) 



ANALYSIS OF TURBULENT FLOW AND HEAT 
TRANSFER ON A FLAT PLATE AT HIGH MACH 
NUMBERS WITH VARIABLE FLUID PROPERTIES. 
R. G. DeiSaler and A. L, Loelfiei, Ji\ Apill 
1958. 61p. diagrs. (NACA TN 4262) 



SUMMARY OF EXPERIMENTAL HEAT-TRANSFER 
MEASUREMENTS IN TURBULENT FLOW FOR A 
MACH NUMBER RANGE FROM 0.87 TO 5.05. 
Maurice J. Brevoort and Barbara D. Arabian. May 
1958. 43p. diagrs., photos., tab. (NACA TN 4248) 



A PERFORMANCE ANALYSIS OF METHODS FOR 
HANDLING EXCESS INLET FLOW AT SUPERSONIC 
SPEEDS. Donald P. Hearth and James F. Connors. 
May 1958. 26p. diagrs., tab. (NACA TN 4270) 



EXPERIMENTAL INVESTIGATION OF AN IMPULSE - 
TYPE SUPERSONIC COMPRESSOR ROTOR HAVING 
A TURNING OF 73° AT THE MEAN RADIUS. James 
R. Sterrett. June 1958. 35p. diagrs., photos., tabs. 
(NACA TN 4252) 



HEAT -TRANSFER AND PRESSURE MEASUREMENTS 
ON FLAT-FACED CYLINDERS AT A MACH NUMBER 
OF 2. William E. Stuney, Jr., and J. Thomas 
Markley. July 1958. 38p. diagrs.. photos., tab. 
(NACA TN 4300) 



EFFECT OF FAVORABLE PRESSURE GRADIENTS 
ON TRANSITION FOR SEVERAL BODIES OF REVO- 
LUTION AT MACH 3.12. John R. Jack. July 1958. 
28p. diagrs., photo. (NACA TN 4313) 



A REVIEW OF THE THERMODYNAMIC, TRANS- 
PORT, AND CHEMICAL REACTION RATE PROP- 
ERTIES OF HIGH-TEMPERATURE AIR 
C. Frederick Hansen and Steve P. Heims. July 1958. 
33p. diagrs. (NACA TN 4359) 



THEORY AND EXPERIMENTS ON SUPERSONIC AIR- 
TO-AIR EJECTORS. (Theorie et experimentation des 
ejecteurs suprrsoniques air-air.) J. Fabri and 
J. Paulon. September 1958. 30p. diagrs. (NACA 
TM 1410. Translation uf Office National d'Etudes et 
de Recherches Aeronautiques. Note Technique 
no. 36. 1956) 



SECOND-ORDER SLENDER-BODY THEORY - 
AX1SYMMETRIC FLOW. Milton D. Van Dyke. 
September 1958. (i), 46p. (NACA TN 4281) 



A MACH 4 ROCKET -POWERED SUPERSONIC TUN- 
NEL USING AMMONIA -OXYGEN AS WORKING 
FLUID. Robert W. Graham, Eleanor Costilow 
Guentert, and Vearl N. Huff. September 1958. 53p. 
diagrs., photos. (NACA TN 4325) 



HYPERSONIC VISCOUS FLOW OVER SLENDER 
CONES. Lawrence Talbot, ToyokiKoga, and 
Pauline M. Sherman, University of California. 
September 1958. 34p. diagrs., photo., tab. 
(NACA TN 4327) 



EFFECT OF SOME EXTERNAL CROSSWISE STIFF- 
ENERS ON THE HEAT TRANSFER AND PRESSURE 
DISTRIBUTION ON A FLAT PLATE AT MACH NUM- 
BERS OF 0.77, 1.39, AND 1.98. Howards. Carter. 
September 1958. 21p. diagrs., photo., tab. 
(NACA TN 4333) 



TABLES AND GRAPHS OF NORMAL-SHOCK PARAM- 
ETERS AT HYPERSONIC MACH NUMBERS AND 
SELECTED ALTITUDES. PaulW. Huber. September 
1958. 26p. diagrs., tabs. (NACA TN 4352) 



SUPERSONIC WAVE INTERFERENCE AFFECTING 
STABILITY. Eugene 3. Love. September 1958. 
19p. diagrs., phutos. (NACA TN 4358. Supersedes 
RM L55L14a) 



AN INVESTIGATION OF SUPERSONIC TURBULENT 
BOUNDARY LAYERS ON SLENDER BODIES OF 
REVOLUTION IN FREE FLIGHT BY USE OF A 
MACH-ZEHNDER INTERFEROMETER AND SHADOW- 
GRAPHS. Alvin Seiff and Barbara J. Short, 
September 1958. 57p. diagrs., photos. 
(NACA TN 4364) 



A STUDY OF SEVERAL THEORETICAL METHODS 
FOR COMPUTING THE ZERO-LIFT WAVE DRAG 
OF A FAMILY OF OPEN -NOSED BODIES OF REVO- 
LUTION IN THE MACH NUMBER RANGE OF 2.0 TO 
4.0. Leroy L. Presley and Emmet A. Mossman. 
September 1958. 61p. diagrs. (NACA TN 4368) 



PRELIMINARY HEAT -TRANSFER STUDIES ON TWO 
BODIES OF REVOLUTION AT ANGLE OF ATTACK 
AT A MACH NUMBER OF 3.12. Norman Sands and 
John R. Jack. September 1958. 29p. diagrs., 
photos., tabs. (NACA TN 4378) 



APPROXIMATE METHOD FOR CALCULATION OF 
LAMINAR BOUNDARY LAYER WITH HEAT TRANS- 
FER ON A CONE AT LARGE ANGLE OF ATTACK 
IN SUPERSONIC FLOW. William E. Brunk. 
September 1958. 26p. diagrs., tab. (NACA TN 4380) 



COMPARISON OF SHOCK-EXPANSION THEORY 
WITH EXPERIMENT FOR THE LIFT, DRAG, AND 
PITCHING-MOMENT CHARACTERISTICS OF TWO 
WING-BODY COMBINATIONS AT M = 5.0. 
Raymond C. Savin. September 1958. 13p. diagrs. 
(NACA TN 4385) 



FREE-FLIGHT INVESTIGATION TO DETERMINE 
THE DRAG OF FLAT- AND VEE-WINDSHIELD 
CANOPIES ON A PARABOLIC FUSELAGE WITH 
AND WITHOUT TRANSONIC INDENTATION 
BETWEEN MACH NUMBERS OF 0.75 AND 1.35. 
Walter L. Kouyoumjian and Sherwood Hoffman. 
September 1958. 34p. diagrs., photos., tabs. 
(NACA TN 4405) 



13 



(1) AERODYNAMICS 



(1.1.3) 
VISCOUS FLOW 



AERODYNAMICS OF SLENDER BODIES AT MACH 
NUMBER OF 3.12 AND REYNOLDS NUMBERS 
FROM 2 x iq6 to 15 x 106. II - AERODYNAMIC 
LOAD DISTRIBUTIONS OF SERIES OF FIVE BODIES 
HAVING CONICAL NOSES AND CYLINDRICAL 
AFTERBODIES. John R. Jack and Lawrence I. 
Gould. May 1952. 2Rp. diagrs., photos., tabs. 
(NACA RM E52C10) 



A PRESSURE -DISTRIBUTION INVESTIGATION OF A 
FINENESS-RATIO-12.2 PARABOLIC BODY OF REV- 
OLUTION (NACA RM- 10) AT M=1.59 AND 
ANGLES OF ATTACK UP TO 36°. Morton Cooper, 
John P. Gapcynski, and Lowell E. Hasel. October 
1952. 89p. diagrs., photos., tabs. 
(NACA RM L52G14a) 



AN INVESTIGATION AT MACH NUMBER 2.40 OF 
FLAP-TYPE CONTROLS EQUIPPED WITH OVER- 
HANG NOSE BALANCES. James N. Mueller. 
November 1953. 95p. diagrs., photos., tab. 
(NACA RM L53I21) 



INVESTIGATION OF SOME WAKE VORTEX CHAR- 
ACTERISTICS OF AN INCLINED OGIVE-CYLINDER 
BODY AT MACH NUMBER 1.98. Leland H. 
Jorgensen and Edward W. Perkins. August 1955. 
47p. diagrs., photos., tabs. (NACA RM A55E31) 



A METHOD FOR THE DESIGN OF POROUS- WALL 
WIND TUNNELS. George M. Stokes. January 

1956. 50p. diagrs., photo., tabs. 
(NACA RM L55J13a) 



VISUALIZATION OF ROTOR TIP SECONDARY 
FLOWS WITH BLADE TIP AIR DISCHARGE AND 
SUCTION IN A LOW-SPEED TURBINE. Milton G. 
Kofski'y andHubert W. Allen. August 1956. 28p. 
diagrs., photos. (NACA RM E56E16) 



SOME EFFECTS OF BLUNTNESS ON BOUNDARY- 
LAYER TRANSITION AND HEAT TRANSFER AT 
SUPERSONIC SPEEDS. W. E. Moeckel. 1957. 
ii, 14p. diagrs. (NACA Rept. 1312. Supersedes 
TN 3653) 



STABILITY OF LAMINAR BOUNDARY LAYER NEAR 
A STAGNATION POINT OVER AN IMPERMEABLE 
WALL AND A WALL COOLED BY NORMAL FLUID 
INJECTION. Morris Morduchow, Richard G. Grape, 
and Richard P . Shaw, Polytechnic Institute of 
Brooklyn. August 1957. 56p. diagrs., tabs. 
(NACA TN 4037) 



STUDY OF PRESSURE DISTRIBUTIONS ON SIMPLE 
SHARP -NOSED MODELS AT MACH NUMBERS FROM 
16 TO 18 TN HELIUM FLOW. Wayne D. Erlckson. 
October 1957. 42p. diagrs., photos. 
(NACATN 4113) 



MOMENTUM TRANSFER FOR FLOW OVER A 
FLAT PLATE WITH BLOWING. H. S. Mickley 
and R. S. Davis, Massachusetts Institute of 
Technology. November 1957. 64p. diagrs., tabs. 
(NACA TN 4017) 



BOUNDARY-LAYER DISPLACEMENT EFFECTS IN 
AIR AT MACH NUMBERS OF 6.8 AND 9.6. 
Mitchel H. Bertram. February 1958. 61p. diagrs., 
photos. (NACA TN 4133) 



INVESTIGATION OF SPOILERS AT A MACH NUM- 
BER OF 1.93 TO DETERMINE THE EFFECTS OF 
HEIGHT AND CHORDWISE LOCATION ON THE 
SECTION AERODYNAMIC CHARACTERISTICS OF 4 
TWO-DIMENSIONAL WING. James N. Mueller. 
February 1958. 52p. diagrs., photos. 
(NACA TN 4180. Supersedes RM L52L31) 



RECOVERY TEMPERATURES AND HEAT TRANS- 
FER NEAR TWO-DIMENSIONAL ROUGHNESS 
ELEMENTS AT MACH 3.1. Paul F. Brinich. 
February 1958. 20p. diagrs. (NACA TN 4213| 



APPROXIMATIONS FOR THE THERMODYNAMIC 
AND TRANSPORT PROPERTIES OF HIGH- 
TEMPERATURE AIR. C Frederick Hansen. 
March 1958. 67p. diagrs., tabs. (NACA TN 4150) 



FREE CONVECTION UNDER THE CONDITIONS OF 
THE INTERNAL PROBLEM. (Svobodnaya convectzia 
v ousloviakh vnoutrennei zadachi.) G. A. Ostroumov. 
April 1958. vii, 233p. diagrs., photos., tabs. 
(NACA TM 1407. Translation of Russian Book, 1952) 



A REVIEW OF THE THERMODYNAMIC, TRANS- 
PORT, AND CHEMICAL REACTION RATE PROP- 
ERTIES OF HIGH-TEMPERATURE AIR. 
C. Frederick Hansen and Steve P. Heims. July 1958. 
33p. diagrs. (NACA TN 4359) 



BOUNDARY-LAYER STABILITY DIAGRAMS FOR 
ELECTRICALLY CONDUCTING FLUIDS IN THE 
PRESENCE OF A MAGNETIC FIELD. Vernon J. 
Rossow. August 1958. 32p. diagrs., tabs. 
(NACA TN 4282) 



ON POSSIBLE SIMILARITY SOLUTIONS FOR 
THREE-DIMENSIONAL INCOMPRESSIBLE LAMINAR 
BOUNDARY-LAYER FLOW OVER DEVELOPABLE 
SURFACES AND WITH PROPORTIONAL MAIN- 
STREAM VELOCITY COMPONENTS. Arthur G. 
Hansen, Case Institute of Technology. September 
1958. (ii), 79p. diagrs. (NACA TM 1437) 



THE TURBULENT BOUNDARY LAYER ON A ROUGH 
CURVILINEAR SURFACE . (Turbulentnyi 
rogranichnyi sloi na sherpokhovatoi krivolineinoi 
poverkhnosti.) V. F. Droblenkov. September 1958. 
lOp. diagrs. (NACA TM 1440. Translation from 
Akademiia Nauk SSSR, Izvestiia, Otdelenie 
Tekhnicheskikh Nauk, no. 8, 1955, p. 17-21) 



NATURAL CONVECTION INSIDE A FLAT ROTATING 
CONTAINER, Simon Ostrach and Willis H. Braun. 
September 1958. 27p. diagrs. (NACA TN 4323) 



A NONLINEAR THEORY FOR PREDICTING THE 
EFFECTS OF UNSTEADY LAMINAR, TURBULENT, 
OR TRANSITIONAL BOUNDARY LAYERS ON THE 
ATTENUATION OF SHOCK WAVES IN A SHOCK 
TUBE WITH EXPERIMENTAL COMPARISON. 
Robert L. Trimpi and Nathaniel B. Cohen. September 
1958. 105p. diagrs., photos., tab. (NACA TN 4347) 



14 



( 1 ) AERODYNAMICS 



SOME NUMERICAL SOLUTIONS OF SIMILARITY 
EQUATIONS FOR THREE-DIMENSIONAL LAMINAR 
INCOMPRESSIBLE BOUNDARY -LAYER FLOWS. 
Peggy L. Yohner and Arthur G. Hansen. September 
1958. 76p. diagrs., tabs. (NACA TN 4370) 



APPROXIMATE SOLUTIONS OF A CLASS OF SIMI- 
LARITY EQUATIONS FOR THREE-DIMENSIONAL, 
LAMINAR, INCOMPRESSIBLE BOUNDARY -LAYER 
FLOWS. Arthur G. Hansen and Howard Z. Herzig. 
September 1958. 26p. diagrs. (NACA TN 4375) 



(1.1.3.1) 
LAMINAR FLOW 



LOAD DISTRIBUTIONS ASSOCIATED WITH CON- 
TROLS AT SUPERSONIC SPEEDS. K. R. Czarnecki 
and Douglas R. Lord. May 1953. 21p. photo., 
diagrs. (NACA RM Lbc'DlGs.) 



INVESTIGATION OF THE AERODYNAMIC CHARAC- 
TERISTICS AT HIGH SUPERSONIC MACH NUMBERS 
OF A FAMILY OF DELTA WINGS HAVING DOUBLE - 
WEDGE SECTIONS WITH THE MAXIMUM THICK- 
NESS AT 0.18 CHORD. Mitchel H. Bertram and 
William D. McCauley. October 1954. 54p. diagrs., 
photos., tabs. (NACA RM L54G28) 



CONTRIBUTIONS ON THE MECHANICS OF 
BOUNDARY-LAYER TRANSITION. G. B. Schubauer 
and P. S. Klebanoff, National Bureau of Standards . 
1956. Ii, lip. diagrs. (NACA Rept. 1289. Super- 
sedes TN 3489) 



EFFECT OF MACH NUMBER ON BOUNDARY- 
LAYER TRANSITION IN THE PRESENCE OF PRES- 
SURE RISE AND SURFACE ROUGHNESS ON AN 
OGIVE -CYLINDER BODY WITH COLD WALL 
CONDITIONS. Robert J. Carros. April 1956. 
30p. diagrs., photos. (NACA RM A56T" w 



AN INVESTIGATION OF FOUR WINGS OF SQUARE 
PLAN FORM AT A MACH NUMBER OF 6.9 IN THE 
LANGLEY 11-INCH HYPERSONIC TUNNEL. 
Charles H. McLellan, Mitchel H. Bertram, and 
John A. Moore. 1957. ii, 18p. diagrs., photos. 
(NACA Rept. 1310. Supersedes RM L51D17) 



EXPLORATORY INVESTIGATION OF BOUNDARY- 
LAYER TRANSITION ON A HOLLOW CYLINDER AT 
A MACH NUMBER OF 6.9. Mitchel H. Bertram. 
1957. ii, 27p. diagrs., photos. (NACA Rept. 1313. 
Supersedes TN 3546) 



INVESTIGATION OF THE LAMINAR AERODYNAMIC 
HEAT -TRANSFER CHARACTERISTICS OF A 
HEMISPHERE-CYLINDER IN THE LANGLEY 
11-INCH HYPERSONIC TUNNEL AT A MACH NUM- 
BER OF 6.8. Davis H. Crawford and William D. 
McCauley. 1957. ii, 21p. diagrs., photos., tab. 
(NACA Rept. 1323. Supersedes TN 3706) 



AVERAGE PROPERlUSS OF COMPRESSIBLE LAM- 
INAR BOUNDARY LAYER ON FLAT PLATE WITH 
UNSTEADY FLIGHT VELOCITY . Franklin K 
Moore and Simon Ostrach. 1957. ill, 12p. diagrs., 
tabs. (NACA Rept. 1325. Supersedes TN 3886) 



ATTENUATION IN A SHOCK TUBE DUE TO 
UNSTEADY-BOUNDARY-LAYER ACTION. Harold 
Mirels. 1957. iii, 19p. diagrs., tab. 
(NACA Rept. 1333. Supersedes TN 3278) 



STABILITY LIMITS AND BURNING VELOCITIES 
FOR SOME LAMINAR AND TURBULENT PROPANE 
AND HYDROGEN FLAMES AT REDUCED PRES- 
SURE. Burton Fine. August 1957. 49p. diagrs., 
tabs. (NACA TN 4031) 



A DISCUSSION OF CONE AND FLAT -PLATE 
REYNOLDS NUMBERS FOR EQUAL RATIOS OF THE 
LAMINAR SHEAR TO THE SHEAR CAUSED BY 
SMALL VELOCITY FLUCTUATIONS IN A LAMINAR 
BOUNDARY LAYER. Neal Tetervin. August 1957. 
25p. diagrs. (NACA TN 4078) 



A THERMAL SYSTEM FOR CONTINUOUS MONI- 
TORING OF LAMINAR AND TURBULENT 
BOUNDARY-LAYER FLOWS DURING ROUTINE 
FLIGHT. Norman R. Richardson and Elmer A. 
Horton. September 1957. 25p. diagrs., photos. 
(NACA TN 4108) 



EFFECTS OF EXTREME SURFACE COOLING ON 
BOUNDARY-LAYER TRANSITION. John R. Jack, 
Richard J. Wisniewski, andN. S. Diaconls. 
(Presented at Symposium on High-Speed Aerodynam- 
ics and Structures, Gainesville, Florida, 
January 22-24, 1957.) October 1957. 19p. diagrs., 
photo. (NACA TN 4094) 



HEAT TRANSFER AND BOUNDARY-LAYER TRAN- 
SITION ON TWO BLUNT BODIES AT MACH NUMBER 
3.12. N. S. Diaconis, Richard J. Wisniewski, and 
John R. Jack. October 1957. 31p. diagrs., photo. 
(NACA TN 4099) 



ON THE SPECTRUM OF NATURAL OSCILLATIONS 
OF TWO-DIMENSIONAL LAMINAR FLOWS/ (Uber 
das Spektrum bei Eigenschwingungen ebener 
Laminarstrbmungen. ) D. Grohne. December 1957. 
34p. diagrs. (NACA TM 1417. Translation from 
Zeitschrift fur angewandte Mathematik und 
Mechanik, v. 34, no. 8-9, August -September 1954, 
p. 344-357) 



VELOCITY AND FRICTION CHARACTERISTICS OF 
LAMINAR VISCOUS BOUNDARY- LAYER AND 
CHANNEL FLOW OVER SURFACES WITH EJEC- 
TION OR SUCTION. E. R. G. Eckert, Patrick L. 
Donoughe and Betty Jo Moore. December 1957. 
57p. diagrs., tabs. (NACA TN 4102) 



HEAT TRANSFER AND RECOVERY TEMPER- 
ATURES ON A SPHERE WITH LAMINAR, TRAN- 
SITIONAL, AND TURBULENT BOUNDARY 
LAYERS AT MACH NUMBERS OF 2.00 AND 4.15. 
Ivan E. Beckwith and James J. Gallagher. 
December 1957. 59p. diagrs., photos. 
(NACA TN 4125) 



EFFECTS OF LEADING-EDGE BLUNTING ON THE 
LOCAL HEAT TRANSFER AND PRESSURE DISTRI- 
BUTIONS OVER FLAT PLATES IN SUPERSONIC 
FLOW. Marcus O. Cr eager. December 1957. 
54p. diagrs., tabs. (NACA TN 4142) 



15 



(1) AERODYNAMICS 



LAMINAR BOUNDARY LAYER WITH HEAT TRANS- 
FER ON A CONE AT ANGLE OF ATTACK IN A 
SUPERSONIC STREAM. Eli Reshotko. December 
1957. (i), 64p. diagrs., tabs. (NACA TN 4152) 



A LOW -SPEED EXPERIMENTAL INVESTIGATION 
OF THE EFFECT OF A SANDPAPER TYPE OF 
ROUGHNESS ON BOUNDARY-LAYER TRANSITION. 
Albert E. von Doenhoff and Elmer A. Horton. 1958. 
ii, 16p. diagrs., photos. (NACA Rept. 1349. 
Supersedes TN 3858) 



EVAPORATION, HEAT TRANSFER, AND VELOC- 
ITY DISTRIBUTION IN TWO-DIMENSIONAL AND 
ROTATIONALLY SYMMETRICAL LAMINAR 
BOUNDARY-LAYER FLOW. (Verdunstung, 
Warmeubergang und Geschwindigkeitsverteilung bei 
zweidimensionaler und rotationssymmetrischer 
laminarer Grenzschichtstromung. ) Nils Frbssling. 
February 1958. 37p. tabs. (NACA TM 1432. 
Translation from Lunds Universitets Arsskrift, 
v. 36, no. 4. Kungl. Fysiografiska Sallskapets 
Handlingar, v. 51, no. 4, 1940) 



INVESTIGATION OF EFFECTS OF DISTRIBUTED 
SURFACE ROUGHNESS ON A TURBULENT BOUND- 
ARY LAYER OVER A BODY OF REVOLUTION AT A 
MACH NUMBER OF 2.01. John R. Sevier, Jr., and 
K. R. Czarnecki. February 1958. 31p. diagrs., 
photos. (NACA TN 4183) 



BOUNDARY-LAYER TRANSITION ON AN OPEN- 
NOSE CONE AT MACH 3.1. Paul F. Brinich. 
February 1958. lip. diagrs. (NACA TN 4214) 



EFFECT OF DISTRIBUTED GRANULAR-TYPE 
ROUGHNESS ON BOUNDARY-LAYER TRANSITION 
AT SUPERSONIC SPEEDS WITH AND WITHOUT SUR- 
FACE COOLING. Albert L. Braslow. March 
1958. 22p. diagrs., photos. (NACA RM L58A17) 



FREE CONVECTION UNDER THE CONDITIONS OF 
THE INTERNAL PROBLEM. (Svobodnaya convectzla 
v ousloviakh vnoutrennei zadachi.) G. A. Ostroumov. 
April 1958. vii, 23 3p. diagrs., photos., tabs. 
(NACA TM 1407. Translation of Russian Book, 1952) 



OBSERVATIONS OF TURBULENT -BURST GEOM- 
ETRY AND GROWTH IN SUPERSONIC FLOW. 
Carlton S. James. April 1958. (i), 85p. diagrs., 
photos., tab. (NACA TN 4235) 



MEASUREMENT OF THE EFFECT OF AN AXIAL 
MAGNETIC FIELD ON THE REYNOLDS NUMBER 
OF TRANSITION IN MERCURY FLOWING THROUGH 
A GLASS TUBE. Michel Bader and William C. A. 
Carlson. May 1958. 8p. diagrs. (NACA TN 4274) 



ON PAIRS OF SOLUTIONS OF A CLASS OF INTER- 
NAL VISCOUS FLOW PROBLEMS WITH BODY 
FORCES. Simon Ostrach and Lynn U. Albers. 
June 1958. 21p. diagrs., tabs. (NACA TN 4273) 



PRANDTL NUMBER EFFECTS ON UNSTEADY 
FORCED-CONVECTION HEAT TRANSFER. E. M. 
Sparrow and J. L. Gregg. June 1958. 14p. diagrs., 
tab. (NACA TN 4311) 



EFFECTS OF BOUNDARY-LAYER DISPLACEMENT 
AND LEADING-EDGE BLUNTNESS ON PRESSURE 
DISTRIBUTION, SKIN FRICTION, AND HEAT TRANS- 
FER OF BODIES AT HYPERSONIC SPEEDS. 
Mitchcl H. Bertram and Arthur Henderson. Jr. 
July 1958. 33p. diagrs. (NACA TN 4301) 



EFFECT OF FAVORABLE PRESSURE GRADIENTS 
ON TRANSITION FOR SEVERAL BODIES OF REVO- 
LUTION AT MACH 3.12. John R . Jack . July 19 58 . 
28p. diagrs., photo. (NACA TN 4313) 



COMPRESSIBLE LAMINAR FLOW AND HEAT 
TRANSFER ABOUT A ROTATING ISOTHERMAL 
DISK. Simon Ostrach and Philip R. Thornton. 
August 1958. 18p. diagrs., tab. (NACA TN 4320) 



ON POSSIBLE SIMILARITY SOLUTIONS FOR 

THREE-DIMENSIONAL INCOMPRESSIBLE LAMINAR 
BOUNDARY-LAYER FLOW OVER DEVELOPABLE 
SURFACES AND WITH PROPORTIONAL MAIN- 
STREAM VELOCITY COMPONENTS. Arthur G. 
Hansen, Case Institute of Technology. September 
1958. (ii), 79p. diagrs. (NACA TM 1437) 



ON FULLY DEVELOPED CHANNEL FLOWS: SOME 
SOLUTIONS AND LIMITATIONS, AND EFFECTS OF 
COMPRESSIBILITY, VARIABLE PROPERTIES, 
AND BODY FORCES. Stephen H. Maslen. September 
1958. 46p. diagrs., tabs. (NACA TN 4319) 



HYPERSONIC VISCOUS FLOW OVER SLENDER 
CONES. Lawrence Talbot, Toyoki Koga, and 
Pauline M. Sherman, University of California. 
September 1958. 34p. diagrs., photo., tab. 
(NACA TN 4327) 



SIMILAR SOLUTIONS FOR THE COMPRESSIBLE 
BOUNDARY LAYER ON A YAWED CYLINDER WITH 
TRANSPIRATION COOLING. Ivan E. Beckwith. 
September 1958. 72p. diagrs., tabs. 
(NACA TN 4345) 



THEORETICAL DISTRIBUTION OF LAMINAR- 
BOUNDARY-LAYER THICKNESS, BOUNDARY- 
LAYER REYNOLDS NUMBER AND STABILITY 
LIMIT, AND ROUGHNESS REYNOLDS NUMBER FOR 
A SPHERE AND DISK IN INCOMPRESSIBLE FLOW. 
Neal Tetervin. September 1958. 36p. diagrs. 
(NACA TN 4350) 



SIMPLIFIED METHOD FOR DETERMINATION OF 
CRITICAL HEIGHT OF DISTRIBUTED ROUGHNESS 
PARTICLES FOR BOUNDARY-LAYER TRANSITION 
AT MACH NUMBERS FROM TO 5. Albert L. 
Braslow and Eugene C. Knox. September 1958. 
18p. diagrs., photos. (NACA TN 4363) 



SOME NUMERICAL SOLUTIONS OF SIMILARITY 
EQUATIONS FOR THREE-DIMENSIONAL LAMINAR 
INCOMPRESSIBLE BOUNDARY -LAYER FLOWS. 
Peggy L. Yohner and Arthur G. Hansen. September 
1958. 76p. diagrs., tabs. (NACA TN 4370) 



APPROXIMATE SOLUTIONS OF A CLASS OF SIMI- 
LARITY EQUATIONS FOR THREE-DIMENSIONAL, 
LAMINAR, INCOMPRESSIBLE BOUNDARY-LAYER 
FLOWS. Arthur G. Hansen and Howard Z. Herzig. 
September 1958. 26p. diagrs. (NACA TN 4375) 



16 



(1) AERODYNAMICS 



ANALYTICAL AND EXPERIMENTAL INVESTIGA- 
TION OF TEMPERATURE RECOVERY FACTORS 
FOR FULLY DEVELOPED FLOW OF AIR IN A 
TUBE. R. G. Deissler, W. F. Wetland, and W. H. 
Lowdermilk. September 1958. 35p. diagrs., tab. 
(NACA TN 4376) 



PRELIMINARY HEAT -TRANSFER STUDIES ON TWO 
BODIES OF REVOLUTION AT ANGLE OF ATTACK 
AT A MACH NUMBER OF 3.12. Norman Sands and 
John R. Jack. September 1958. 29p. diagrs., 
photos., tabs. (NACA TN 4378) 



APPROXIMATE METHOD FOR CALCULATION OF 
LAMINAR BOUNDARY LAYER WITH HEAT TRANS- 
FER ON A CONE AT LARGE ANGLE OF ATTACK 
IN SUPERSONIC FLOW. William E. Brunk. 
September 1958. 26p. diagrs., tab. {NACA TN 4380) 



EFFECTS OF NOSE ANGLE AND MACH NUMBER 
ON TRANSITION ON CONES AT SUPERSONIC 
SPEEDS. K. R. Czarnecki and Mary W. Jackson. 
Seple ruber 1958. 17p. diagrs., photo. 
(NACA TN 4388) 



MASS TRANSFER COOLING NEAR THE STAGNATION 
POINT. Leonard Roberts. September 1958. 42p. 
diagrs. (NACA TN 4391) 



A THEORETICAL STUDY OF STAGNATION -POINT 
ABLATION. Leonard Roberts. September 1958. 
29p. diagrs. (NACA TN 4392) 



(1. 1.3.2) 
TURBULENT FLOW 



LOAD DISTRIBUTIONS ASSOCIATED WITH CON- 
TROLS AT SUPERSONIC SPEEDS. K. R. Czarnecki 
and Douglas R. Lord. May 1953. 21p. photo., 
diagrs. (NACA RM L 5 3D 15 a) 



TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF TAPER RATIO, BODY INDEN- 
TATION, FDCED TRANSITION, AND AFTERBODY 
SHAPE ON THE AERODYNAMIC CHARACTERIS- 
TICS OF A 45° SWEPTBACK WING-BODY COMBI- 
NATION. Francis G. Morgan, Jr., and Melvin M. 
Carmel. March 1954. 37p. diagrs., tab. 
(NACA RM L54A15) 



LOW-VELOCITY TURNING AS A MEAN, OF MINI- 
MIZING BOUNDARY -LAYER ACCUMULATIONS 
RESULTING FROM SECONDARY FLOWS WITHIN 
TURBINE STATORS. Warner L. Stewart and Robert 
Y. Wong. May 1954. 18p. diagrs., photo. 
(NACARME54B16) 



FLIGHT MEASUREMENTS OF AVERAGE SKIN- 
FRICTION COEFFICIENTS ON A PARABOLIC BODY 
OF REVOLUTION (NACA RM-10) AT MACH NUM- 
ERS FROM 1.0 TO 3.7. J. Dan Lo poser and 
Charles B. Rumsey. August 1954. 32p. diagrs., 
photos. (NACA RM L54G14) 



THE EFFECT OF FLUID INJECTION ON THE COM- 
PRESSIBLE TURBULENT BOUNDARY LAYER - 
PRELIMINARY TESTS ON TRANSPIRATION COOL- 
ING OF A FLAT PLATE AT M = 2.7 WITH AIR AS 
THE INJECTED GAS. Morris W. Rubesin, 
Constantine C. Pappas, and Arthur F. Okuno. 
December 1955. 37p. diagrs. (NACA RM A55I19) 



CONTRIBUTIONS ON THE MECHANICS OF 
BOUNDARY-LAYER TRANSITION. G- B. Schubauer 
and P. S. Klebanoff, National Bureau of Standards. 
1956. ii, lip. diagrs. (NACA Rept. 1289. Super- 
sedes TN 3489) 



THE INFLUENCE OF SURr ACE INJECTION ON 
HEAT TRANSFER AND SKIN FRICTION ASSOCI- 
ATED WITH THE HIGH-SPEED TURBULENT 
BOUNDARY LAYER. Morris W. Rubesin. 
February 1956. 16p. diagrs. (NACA RM A55L13) 



EFFECT OF MACH NUMBER ON BOUNDARY - 
LAYER TRANSITION IN THE PRESENCE OF PRES- 
SURE RISE AND SURFACE ROUGHNESS ON AN 
OGIVE-CYLINDER BODY WITH COLD WALL 
CONDITIONS. Robert J. Carros. April 1956. 
30p. diagrs., photos. (NACA RM A56B15) 



LIGHT DIFFUSION THROUGH HIGH-SPEED TURBU- 
LENT BOUNDARY LAYERS. Howard A. Stine and 
Warren Winovich. May 1958. 46p. diagrs., 
photos., tabs. (NACA RM A56B21) 



EXPERIMENTAL INVESTIGATION OF INTERFER- 
ENCE EFFECTS OF LATERAL -SUPPORT STRUTS 
ON AFTERBODY PRESSURES AT MACH 1.9. John 
L. Klann and Ronald G. Huff. May 1956. I3p. 
diagrs., tab. (NACA RM E56C16) 



THE EFFECT OF FLUID INJECTION ON THE 
COMPRESSIBLE TURBULENT BOUNDARY LAYER 
- THE EFFECT ON SKIN FRICTION OF AIR 
INJECTED INTO THE BOUNDARY LAYER OF A 
CONE AT M = 2.7. Thorval Tendeland and Arthur 
F. Okuno. June 1956. 23p. diagrs. 
(NACA RM A56D05) 



EXPLORATORY INVESTIGATION OF BOUNDARY- 
LAYER TRANSITION ON A HOLLOW CYLINDER AT 
A MACH NUMBER OF 6.9. Mitchel H. Bertram. 
1957. ii, 27p. diagrs., photos. (NACA Rept. 1313. 

Supersedes TN 3546) 



AN EVALUATION OF FOUR EXPERIMENTAL 
METHODS FOR MEASURING MEAN PROPERTIES 
OF A SUPERSONIC TURBULENT BOUNI \ Y 
LAYER. George J. Nothwang. 1957. ^ . ■■:->. 
diagrs., photos. (NACA Rept. 1320. Supt .< ? --, i ,.<■-> 
TN 3721) 



ATTENUATION IN A SHOCK TUBE DUE TC 
UNSTEADY -BOUNDARY-LAYER ACTION. Harold 
Mirels. 1957. iii, 19p. diagrs., tab. 
(NACA Rept. 1333. Supersedes TN 3278) 



AN INVESTIGATION OF FLOW IN CIRCULAR AND 
ANNULAR 90° BENDS WITH A TRANSITION IN 
CROSS SECTION. Stafford W. Wilbur. August 
1957. 32p. diagrs., photos., tabs. (NACA TN 3995) 



( 1 ) AERODYNAMICS 



17 



STABILITY LIMITS AND BURNING VELOCITIES 
FOR SOME LAMINAR AND TURBULENT PROPANE 
AND HYDROGEN FLAMES AT REDUCED PRES- 
SURE. Burton Fine. August 1957. 49p. diagrs,, 
tabs. (NACA TN 4031) 



A DISCUSSION OF CONE AND FLAT-PLATE 
REYNOLDS NUMBERS FOR EQUAL RATIOS OF THE 
LAMINAR SHEAR TO THE SHEAR CAUSED BY 
SMALL VELOCITY FLUCTUATIONS IN A LAMINAR 
BOUNDARY LAYER. Neal Tetervin. August 1957. 
25p. diagrs. (NACA TN 4078) 



THE PRINCIPLES OF TURBULENT HEAT TRANS- 
FER. (Die Grundlagen dos Turbulenten 
Warmeuberganges . ) H. Reichardt. September 
1957. 45p. diagrs., tabs. (NACA TM 1408. 
Translation from Archiv fur die gesamte 
Warmetechnik, no. 6/7, 1951, p. 129-142) 



A THERMAL SYSTEM FOR CONTINUOUS MONI- 
TORING OF LAMINAR AND TURBULENT 
BOUNDARY-LAYER FLOWS DURING ROUTINE 
FLIGHT. Norman R. Richardson and Elmer A. 
Horton. September 1957. 25p. diagrs., photos. 
(NACA TN 4108) 



INFLUENCE OF TURBULENCE ON TRANSFER OF 
HEAT FROM CYLINDERS. J. Kestin and P. F. 
Maeder, Brown University. October 1957. 78p. 
diagrs., tabs. (NACA TN 4018) 



EXPERIMENTAL INVESTIGATION OF TRANSPIRA- 
TION COOLING FOR A TURBULENT BOUNDARY 
LAYER IN SUBSONIC FLOW USING AIR AS A 
COOLANT. William E. Brunk. October 1957. 
35p. diagrs. {NACA TN 4091) 



EFFECTS OF EXTREME SURFACE COOLING ON 
BOUNDARY-LAYER TRANSITION. John R.Jack, 
Richard J. Wisniewski, andN. S. Diaconls. 
(Presented at Symposium on High-Speed Aerodynam- 
ics and Structures, Gainesville, Florida, 
January 22-24, 1957.) October 1957. 19p. diagrs., 
photo. (NACA TN 4094) 



HEAT TRANSFER AND BOUNDARY -LAYER TRAN- 
SITION ON TWO BLUNT BODIES AT MACH NUMBER 
3.12. N. S. Diaconis, Richard J. Wisniewski, and 
John R. Jack October 1957. 31p. diagrs., photo. 
(NACA TN 4099) 



TURBULENCE MEASUREMENTS IN MULTIPLE 
INTERFERING AIR JETS. James C. Laurence and 
Jean M. Benninghoff. December 1957. 37p. 
diagrs., photos. (NACA TN 4029) 



HEAT TRANSFER AND RECOVERY TEMPER- 
ATURES ON A SPHERE WITH LAMINAR, TRAN- 
SITIONAL, AND TURBULENT BOUNDARY 
LAYERS AT MACH NUMBERS OF 2.00 AND 4.15. 
Ivan E. Beckwith and James J. Gallagher. 
December 1957. 59p. diagrs., photos. 
(NACA TN 4125) 



APPROXIMATE CALCULATION OF THE COMPRES- 
SIBLE TURBULENT BOUNDARY LAYER WITH 
HEAT TRANSFER AND ARBITRARY PRESSURE 
GRADIENT. Eli Reshotko and Maurice Tucker. 
December 1957. 34 p. diagrs. (NACA TN 4154) 



A LOW-SPEED EXPERIMENTAL INVESTIGATION 
OF THE EFFECT OF A SANDPAPER TYPE OF 
ROUGHNESS ON BOUNDARY -LAYER TRANSITION. 
Albert E. von Doenhoff and Elmer A. Horton. 1958. 
ii, 16p. diagrs., photos. (NACA Rept. 1349. 
Supersedes TN 3858) 



ON THE STATISTICAL THEORY OF TURBULENCE. 

(Zur statistischen Theorie der Turbulenz). 
W. Heisenberg. January 1958. 36p. diagrs. 
(NACA TM 1431. Translation from Zeitschrift fur 
Physik, v.124, 1948, p. 628-657) 



TURBULENT BOUNDARY LAYER ON A YAWED 
CONE IN A SUPERSONIC STREAM. Willis H. 
Braun. January 1958. 39p. diagrs. 
(NACA TN 4208) 



AN ANALYSIS OF THE TURBULENT BOUNDARY- 
LAYER CHARACTERISTICS ON A FLAT PLATE 
WITH DISTRIBUTED LIGHT -GAS INJECTION. 
Morris W. Rubcsin and Constantine C- Pappas. 
February 1958. 43p. diagrs. (NACA TN 4149) 



INVESTIGATION OF EFFECTS OF DISTRIBUTED 
SURFACE ROUGHNESS ON A TURBULENT BOUND- 
ARY LAYER OVER A BODY OF REVOLUTION AT A 
MACH NUMBER OF 2.01. John R. Sevier, Jr., and 
K. R. Czarnecki. February 1958. 31p. diagrs., 
photos. (NACA TN 4183) 



BOUNDARY-LAYER TRANSITION ON AN OPEN- 
NOSE CONE AT MACH 3.1. Paul F. Brinich. 
February 1958. lip. diagrs. (NACA TN 4214) 



EFFECT OF DISTRIBUTED GRANULAR-TYPE 
ROUGHNESS ON BOUNDARY-LAYER TRANSITION 
AT SUPERSONIC SPEEDS WITH AND WITHOUT SUR- 
FACE COOLING. Albert L. Braslow. March 
1958. 22p. diagrs., photos. (NACA RM L58A17) 



WALL PRESSURE FLUCTUATIONS IN A TURBU- 
LENT BOUNDARY LAYER. William W. Willmarth, 
Calif ornia Institute of Technology. March 1958. 
39p. diagrs., photo. (NACA TN 4139) 



EFFECT OF WALL COOLING ON INLET PARAME- 
TERS OF A SCOOP OPERATING IN A TURBULENT 
BOUNDARY LAYER ON A FLAT OR CONICAL SUR- 
FACE FOR MACH NUMBERS 2 TO 10. Andrew Beke. 
March 1958. 21p. diagrs., tabs. 
(NACA TN 4153) 



SKIN-FRICTION MEASUREMENTS IN INCOMPRES- 
SIBLE FLOW. Donald W. Smith and John H. Walker. 
March 1958. 67p. diagrs., photo., tabs. 
(NACA TN 4231) 



TURBULENT SHEARING STRESS IN THE BOUND- 
ARY LAYER OF YAWED FLAT PLATES. 
Harry Ashkenas, Cornell University. April 1958. 
58p. diagrs., photos., tab. (NACA TN 4140) 



OBSERVATIONS OF TURBULENT -BURST GEOM- 
ETRY AND GROWTH IN SUPERSONIC FLOW. 
Carlton S. James. April 1958. (i), 85p. diagrs., 
photos., tab. (NACA TN 4235) 



18 



(1) AERODYNAMICS 



EFFECTS OF MACH NUMBER AND WALL- 
TEMPERATURE RATIO ON TURBULENT HEAT 
TRANSFER AT MACH NUMBERS FROM 3 TO 5. 
Thorval Tendeland. April 1958. 46p. diagrs. 
(NACA TN 4236) 



ANALYSIS OF TURBULENT FLOW AND HEAT 
TRANSFER ON A FLAT PLATE AT HIGH MACH 
NUMBERS WITH VARIABLE FLUID PROPERTIES. 
R. G. Deissler and A. L. Loeffler, Jr. April 
1958. 61p. diagrs. (NACA TN 4262) 



LOCAL ISOTROPY IN TURBULENT SHEAR FLOW. 
Stanley Corrsin. Johns Hopkins University May 
1958. " 15p. dlagr. (NACA RM 58B11) 



SUMMARY OF EXPERIMENTAL HEAT-TRANSFER 
MEASUREMENTS IN TURBULENT FLOW FOR A 
MACH NUMBER RANGE FROM 0.87 TO 5.05. 
Maurice J. Brevoort and Barbara D. Arabian. May 
1958. 43p. diagrs., photos., tab. (NACA TN 4248) 



MEASUREMENT OF THE EFFECT OF AN AXIAL 
MAGNETIC FIELD ON THE REYNOLDS NUMBER 
OF TRANSITION IN MERCURY FLOWING THROUGH 
A GLASS TUBE. Michel Bader and William C. A. 
Carlson. May 1958. 8p. diagrs. (NACA TN 4274) 



HEAT TRANSFER IN ISOTROPIC TURBULENCE 
DURING THE FINAL PERIOD OF DECAY. D. W. 
Dunn and W. H. Reid, Johns Hopkins University 
and Ballistic Research Laboratories, U. S. Army. 
June 1958. 68p. diagrs., tabs. (NACA TN 4186) 



AN EXPERIMENTAL STUDY OF THE TURBULENT 
BOUNDARY LAYER ON A SHOCK-TUBE WALL. 
Paul B. Gooderum. June 1958. 63p. diagrs., 
photos., tab. (NACA TN 4243) 



STATISTICAL STUDY OF TURBULENCE - SPEC- 
TRAL FUNCTIONS AND CORRELATION COEFFI- 
CIENTS. (Etude statistique de la turbulence. 
Fonctions spectrales et coefficients de correlation.) 
Francois N. Frenkiel. July 1958. Il6p. diagrs., 
tabs. (NACA TM 1436. Translation of Office 
National d'Etudes et de Recherches Aeronautiques. 
Rapport Technique no. 34, 1948) 



EFFECTS OF FABRICATION-TYPE ROUGHNESS ON 
TURBULENT SKIN FRICTION AT SUPERSONIC 
SPEEDS. K. R. Czarnecki, John R. Sevier, Jr., 
and Melvin M. Carmel. July 1958. 15p. diagrs. 
(NACA TN 4299) 



EFFECT dF FAVORABLE PRESSURE GRADIENTS 
ON TRANSITION FOR SEVERAL BODIES OF REVO- 
LUTION AT MACH 3.12. John R. Jack. July 1958. 
28p. diagrs., photo. (NACA TN 4313) 



AN ESTIMATE OF THE FLUCTUATING SURFACE 
PRESSURES ENCOUNTERED IN THE REENTRY OF 
A BALLISTIC MISSILE. Edmund E. Callaghan. 
July 1958. 18p. diagrs. (NACA TN 4315) 



INFLUENCE OF SOLID-BODY ROTATION ON 
SCREEN-PRODUCED TURBULENCE. Stephen C. 
Traugott, Johns Hopkins University. August 1958. 
lOOp. diagrs., photos. (NACA TN 4135) 



TURBULENCE AND TEMPERATURE FLUCTUA- 
TIONS BEHIND A HEATED GRID. R. R. Mills, Jr., 
A. L. Kistler, V. O'Brien, and S. Corrsin, Johns 
Hopkins University. August 1958. 67p. diagrs. 
(NACA TN 4288) 



THE TURBULENT BOUNDARY LAYER ON A ROUGH 

CURVILINEAR SURFACE . (Turbulentnyi 
rogranichnyi sloi na sherpokhovatoi krivolineinoi 
poverkhnosti.) V. F. Droblenkov. September 1958. 
lOp. diagrs. (NACA TM 1440. Translation from 
Akademiia Nauk SSSR, Izvestiia, Otdelenie 
Tekhnicheskikh Nauk, no. 8, 1955, p. 17-21) 



AN ANALYTICAL STUDY OF TURBULENT AND 
MOLECULAR MIXING IN ROCKET COMBUSTION. 
David A. Bittker. September 1958. 22p. diagrs. 
(NACA TN 4321) 



EFFECT OF SOME EXTERNAL CROSSWISE STIFF- 
ENERS ON THE HEAT TRANSFER AND PRESSURE 
DISTRIBUTION ON A FLAT PLATE AT MACH NUM- 
BERS OF 0.77, 1-39, AND 1.98. Howards. Carter. 
September 1958. 21p. diagrs., photo., tab. 
(NACA TN 4333) 



SIMPLIFIED METHOD FOR DETERMINATION OF 
CRITICAL HEIGHT OF DISTRIBUTED ROUGHNESS 
PARTICLES FOR BOUNDARY-LAYER TRANSITION 
AT MACH NUMBERS FROM TO 5. Albert L. 
Braslow and Eugene C. Knox. September 1958. 
18p. diagrs., photos. (NACA TN 4363) 



AN INVESTIGATION OF SUPERSONIC TURBULENT 
BOUNDARY LAYERS ON SLENDER BODIES OF 
REVOLUTION IN FREE FLIGHT BY USE OF A 
MACH-ZEHNDER INTERFEROMETER AND SHADOW- 
GRAPHS. Alvin Seiff and Barbara J. Short. 
September 1958. 57p. diagrs., photos. 
(NACA TN 4364) 



ANALYTICAL AND EXPERIMENTAL INVESTIGA- 
TION OF TEMPERATURE RECOVERY FACTORS 
FOR FULLY DEVELOPED FLOW OF AIR IN A 
TUBE. R. G. Deissler, W. F. Weiland, and W. H. 
Lowdermilk. September 1958. 35p. diagrs., tab. 
(NACA TN 4376) 



PRELIMINARY HEAT -TRANSFER STUDIES ON TWO 
BODIES OF REVOLUTION AT ANGLE OF ATTACK 
AT A MACH NUMBER OF 3.12. Norman Sands and 
John R. Jack. September 1958. 29p. diagrs., 
photos., tabs. (NACA TN 4378) 



ANALYSIS OF TURBULENT FLOW AND HEAT 
TRANSFER IN NONCIRCULAR PASSAGES. Robert 
G. Deissler and Maynard F. Taylor. September 
1958. 35p. diagrs. (NACA TN 4384) 



(1. 1.3. 3) 
JET MIXING 



INVESTIGATION AT MACH NUMBER 1.91 OF SIDE 
AND BASE PRESSURE DISTRIBUTIONS OVER CONI- 
CAL BOATTAILS WITHOUT AND WITH JET FLOW 
ISSUING FROM BASE. Edgar M. Cortright, Jr., and 
Albert H. Schroeder. September 1951. 59p. diagrs., 
photos. (NACA RM E51F26) 



(1) AERODYNAMICS 



19 



SPREADING OF EXHAUST JET FROM 16-INCH RAM 
JET AT MACH NUMBER 2.0. Fred Wilcox and 
Donald Pennington. August 1952. 14p. diagrs., 
photo., tab. (NACA RM E52F25) 



SOME EFFECTS OF A SONIC JET EXHAUST ON 
THE LOADING OVER A YAWED FIN AT A MACH 
NUMBER OF 3.03. John E. Hatch, Jr., and William 
M. Savelle. January 1953. 12p. diagrs., photo. 
(NACA RM L52L02a) 



SOME MEASUREMENTS OF FLYING QUALITIES OF 
A DOUGLAS D-558-H RESEARCH AIRPLANE DUR- 
ING FLIGHTS TO SUPERSONIC SPEEDS. Herman O. 
Ankenbruck and Theodore E. Dahlen. March 1953. 
25p. diagrs., photos., tab. (NACA RM L53A06) 



JET EFFECTS ON FLOW OVER AFTERBODIES IN 
SUPERSONIC STREAM. Edgar M. Cortright, Jr., 
and Fred D. Kochendorfer. November 1953. 31p. 
diagrs., photos. (NACA RM E53H25) 



PRELIMINARY INVESTIGATION OF PUMPING AND 
THRUST CHARACTERISTICS OF FULL-SIZE 
COOLING-AIR EJECTORS AT SEVERAL EXHAUST- 
GAS TEMPERATURES. W. K. Greathouse. April 
1954. 130p. diagrs., photos., tab, 
(NACA RM E54A18) 



TRANSONIC FLIGHT TEST OF A ROCKET - 
POWERED MODEL TO DETERMINE PROPULSIVE 
JET INFLUENCE ON THE CONFIGURATION DRAG. 

Carlos A. deMoraes. June 1954. 16p. diagrs., 
photo. (NACA RM L54D27) 



EXPERIMENTAL DATA FOR FOUR FULL-SCALE 
CONICAL COOLING-AIR EJECTORS. C. C. 
Ciepluch and D. B. Fenn. November 1954. 41p. 
diagrs., photo., tab. (NACA RM E54F02) 



PHOTOGRAPHIC INVESTIGATION OF AIR -FLOW 
PATTERNS IN TRANSPARENT ONE-SLXTH SECTOR 
OF ANNULAR TURBOJET-ENGINE COMBUSTOR 
WITH AXIAL-SLOT -TYPE AIR ADMISSION. 
Charles C. Graves and J. Dean Gernon. December 
19 54 . 24p . diagrs . , photos . (NACA RM E 54128a) 



INVESTIGATION AT SUPERSONIC SPEEDS OF THE 
EFFECT OF JET MACH NUMBER AND DIVER- 
GENCE ANGLE OF THE NOZZLE UPON THE PRES- 
SURE OF THE BASE ANNULUS OF A BODY OI 
REVOLUTION. August F. Bromm, Jr., and Robert 
M. O'Donnell. December 1954. 24p. diagrs., 
photos. (NACA RM L54I16) 



JET EFFECTS ON LONGITUDINAL TRIM OF AN 
AIRPLANE CONFIGURATION MEASURED AT MACH 
NUMBERS BETWEEN 1.2 AND 1.8. Robert F. Peck. 
January 1955. 17p. diagrs., photos. 
(NACARM L54J29a) 



PRELIMINARY INVESTIGATION OF A TECHNIQUE 
OF PRODUCING A HEATED CORE IN A SUPER- 
SONIC WIND-TUNNEL STREAM. Morris D. 
Rousso and Milton A. Beheim. February 1955. 
22p. photos., diagrs. (NACA RM E54K02) 



SOME STUDIES OF AXISYMMETRIC FREE JETS 
EXHAUSTING FROM SONIC AND SUPERSONIC 
NOZZLES INTO STILL AIR AND INTO SUPERSONIC 
STREAMS. Eugene's. Love and Carl E. Grigsby. 
May 1955. il, 178p. diagrs., photos., tabs. 
(NACA RM L54L31) 



A FREE-FLIGHT INVESTIGATION OF THE EFFECTS 
OF SIMULATED SONIC TURBOJET EXHAUST ON 
THE DRAG OF A BOATTAIL BODY WITH VARIOUS 
JET SIZES FROM MACH NUMBER 0.87 TO 1.50. 
Ralph A. Falanga. August 1955. 23p. diagrs., 
photos., tab. (NACA RM L55F09a) 



FREE -FLIGHT TESTS TO DETERMINE THE 
POWER -ON AND POWER -OFF PRESSURE DISTRI- 
BUTION AND DRAG OF THE NACA RM-10 RE- 
SEARCH VEHICLE AT LARGE REYNOLDS NUM- 
BERS BETWEEN MACH NUMBERS 0.8 AND 3.0, 
Sherwood Hoffman. September 1955. 55p. diagrs., 
photos., 3 tabs. (NACA RM L55H02) 



INITIAL INCLINATION OF THE MLXING BOUNDARY 
SEPARATING AN EXHAUSTING SUPERSONIC JET 
FROM A SUPERSONIC AMBIENT STREAM. 
Eugenes. Love. January 1956. 30p. diagrs. 
(NACA RM L55J14) 



A FREE -FLIGHT INVESTIGATION OF THE EF- 
FECTS OF A SONIC JET ON THE TOTAL-DRAG 
And BASE -PRESSURE COEFFICIENTS OF A BOAT- 
TAIL BODY OF REVOLUTION FROM MACH NUM- 
BER 0.83 TO 1.70. Ralph A. Falanga. March 1956. 
18p. diagrs., pho'o., tab. (NACA RM L55L21) 



JET EFFECTS ON BASE AND AFTERBODY PRES- 
SURES OF A CYLINDRICAL AFTERBODY AT TRAN- 
SONIC SPEEDS. James M. Cubbage, Jr. May 1956. 
50p. diagrs., photos. (NACA RM L56C21) 



BOUNDARIES OF SUPERSONIC AXISYMMETRIC 
FREE JETS. EugeneS. Love, Mildred J. Woodling, 
and Louise P. Lee. October 1956. 98p. diagrs. 
(NACARM L56G18) 



FREE-FLIGHT INVESTIGATION AT TRANSONIC 
SPEEDS OF DRAG COEFFICIENTS OF A BOATTAIL 
BODY OF REVOLUTION WITH A SIMULATED TUR- 
BOJET EXHAUST ISSUING AT THE BASE FROM 
CONICAL SHORT-LENGTH EJECTORS. Ralph A. 
Falanga and Abraham Leiss. December 19G6. 34p. 
diagrs., photos., tab. (NACA RM L56H23) 



FAR NOISE FIELD OF AIR JETS AND JET ENGINES. 
Edmund E. Callaghan and WiUard D. Coles. 1957. 
ii, 18p. diagrs., photos. (NACA Rept. 1329. 
Supersedes TN 3590; TN 3591) 



NEAR NOISE FIELD OF A JET-ENGINE EXHAUST. 
Walton L. Howes, Edmund E. Callaghan, WiUard D. 
Coles, and Harold R. Mull. Appendix B: CORRE- 
LATION COMPUTER. Channing C. Conger and . 
Donald F. Berg. 1957. ii, 35p. diagrs., photos., 
tab. (NACA Rept. 1338. Supersedes TN 3763 and 
TN 3764) 



20 



(1) AERODYNAMICS 



TURBULENCE MEASUREMENTS IN MULTIPLE 
INTERFERING AIR JETS. James C. Laurence and 
JeanM. Benninghoff. December 1957. 37p. 
diagrs., photos. (NACA TN 4029) 



SHAPE OF INITIAL PORTION OF BOUNDARY OF 
SUPERSONIC AXISYMMETRIC FREE JETS AT 
LARGE JET PRESSURE RATIOS. Eugene S. Love 
and Louise P. Lee. January 1958. 29p. diagrs 
(NACA TN 4195) 



LIMITED INVESTIGATION OF NOISE SUPPRESSION 
BY INjhiC HON OF WATER INTO EXHAUST OF 
AFTERBURNING JET ENGINE. Max C. Kurbjun. 
February 1958. 15p. diagrs., photo. 
(NACA RM L57L05) 



EFFECT OF JET TEMPERATURE ON JET-NOISE 
GENERATION. Vern G. Rollin. March 1958. 
13p. diagrs., photo. (NACA TN 4?17) 



USE OF THE COANDA EFFECT FOR OBTAINING 
JET DEFLECTION AND LIFT WITH A SINGLE 
FLAT-PLATE DEFLECTION SURFACE. Uwe H. 
vonGlahn. June 1958. 49p. diagrs., tabs. 
(NACA TN 4272) 



TURBOJET ENGTNE NOISE REDUCTION WITH NflX- 
ING NOZZLE-EJECTOR COMBINATIONS. Willard 
D. Coles, John A. Mihaloew, and Edmund E. 
Callaghan. August 1958. 33p. diagrs., photos., 
t^b. (NACA TN 4317) 



THEORY AND EXPERIMENTS ON SUPERSONIC AIR- 
TO-AIR EJECTORS. (Theone i;t experimentation des 

ejecteurs supert^uniques air-air ) J. Fabri and 
J. Paulon. September 1958. 30p. dia : ;rs (NACA 
TM 1410. Translation uf Office National d'Eiudes vi 
de Rechorches Aeronautiques. Note Technique 
no. 36, 1956) 



EXPERIMENTAL INVESTIGATION OF AXIAL AND 
NORMAL FORCE CHARACTERISTICS OF SKEWED 
NOZZLES. David J. Carter, Jr., and Allen R. 
Virk. September 1958. 40p. diagrs.. photos. 
(NACA TN 4336) 



USE OF THE COANDA EFFECT FOR JET DEFLEC- 
TION AND VERTICAL LIFT WITH MULTIPLE FLAT- 
PLATE AND CURVED-PLATE DEFLECTION SUR- 
FACES. Uwe H. von Glahn. APPENDIX B: 
ESTIMATED PERFORMANCE OF MULTIPLE-FLAT- 
PLATE DEFLECTORS. Thomas F. Geldei . 
September 1958. 54p. diagrs., photo., Jabs. 
(NACA TN 4377) 



EFFECTS OF GROUND PROXIMITY ON THE 
THRUST OF A SIMPLE DOWNWARD-D'^ECTED JET 
BENEATH A FLAT SURFACE. Kenneth P. 
Spreemann and Irving R. Sherman. September 1958. 
39p. diagrs., photos. (NACA TN 4407) 



(U.4) 
AERODYNAMICS WITH HEAT 



PRELIMINARY INVESTIGATION OF PUMPING AND 
THRLST CHARACTERISTICS OF FULL-SIZE 
COOLING-AIR EJECTORS AT SEVERAL EXHAUST- 
GAS TEMPERATURES. W. K. Greathouse. April 
1954. I30p. diagrs., photos., tab 
(NACA RM E54A18) 



FLIGHT MEASUREMENTS OF AVERAGE SKIN- 
FRICTION COEFFICIENTS ON A PARABOLIC BODY 
OF REVOLUTION (NACA RM-10) AT MACH NUM- 
ERS FROM 1.0 TO 3.7. J. Dan Loposer and 
Charles B. Rumsey. August 1954. 32p. diagrs., 
photos. (NACA RM L54G14) 



SOME EFFECTS OF BLUNTNESS ON BOUNDARY^ 
LAYER TRANSITION AND HEAT TRANSFER AT 
SUPERSONIC SPEEDS. W. E. Moeckel. 1957. 
ii, 14p. diagrs. (NACA Rept. 1312. Supersedes 
TN 3653) 



STABILITY OF LAMINAR BOUNDARY LAYER NEAR 
A STAGNATION POINT OVER AN IMPERMEABLE 
WALL AND A WALL COOLED BY NORMAL FLUID 
INJECTION. Morris Morduchow, Richard G. Grape, 
and Richard P. Shaw, Polytechnic Institute of 
Brooklyn. August 1957. 56p. diagrs., tabs. 
(NACA TN 4037) 



EXPLORATORY INVESTIGATION Ol KTA : '> - \M> 
BASE-PRESSURE INCREASES RESULTING MfOM 
COMBUSTION OF ALUMINUM BOROHYDR1DF. 
ADJACENT TO BODY OF REVOLUTION IN SUPER- 
SONIC WIND TUNNEL. John S. Scrafini. Robert G. 
Borsch, and Edward A FU:t.:her. October 1957 
49p. diagrs., photos., tabs. (NACA RM E57E15) 



A COMPARATIVE ANALYSIS OF THE PERFORM- 
ANCE OF LONG-RANGE HYPERVELOCITY 
VEHICLES. Alfred J. Eggers, Jr., H. Julian Allen, 
and Stanford E. Neice. October 1957. (i), 66p. 
diagrs. (NACA TN 4046. Supersedes RM A54L10) 



A STUDY OF THE MOTION AND AERODYNAMIC 
HEATING OF MISSILES ENTERING THE EARTH'S 
ATMOSPHERE AT HIGH SUPERSONIC SPEEDS. 
H. Julian Allen and A. J. Eggers, Jr. October 
1957. 6 lp. diagrs. (NACA TN 4047. Supersedes 
RM A53D28) 



EFFECTS OF EXTREME SURFACE COOLING ON 
BOUNDARY -LAYER TRANSITION. John R. Jack, 
Richard J. Wisniewski. and N. S. Diuconis. 
(Presented at Symposium on High-Speed Aerodynam- 
ics and Structures, Gainesville, Florida, 
January 22-24, 1957.) October 195*. 19p. diagrs., 
photo. (NACA TN 4094) 



DEVELOPMENT OF A PISTON-COMPRESSOR TYPE 
IJGHT-GAS GUN FOR THE LAUNCHING OF FREE- 
FLIGHT MODELS AT HIGH VELOCITY. A. C . 
Charters, B. PatDenardo, and Vernon J. Rossow. 
November 1957. (i), 95p. diagrs., photos., tabs. 
(NACA TN 4143. Supersedes RM A55G11) 



(1) AERODYNAMICS 



21 



EFFECT OF OXYGEN RECOMBINATION ON ONE- 
DIMENSIONAL FLOW AT HIGH MACH NUMBERS. 
Steve P. Heims. January 1958. 52p. diagrs. 
(NACA TN 4144) 



PRANDTL-MEYER EXPANSION OF CHEMICALLY 
REACTING GASES IN LOCAL CHEMICAL AND 
THERMODYNAMIC EQUILIBRIUM. Steve P. Heims. 
March 1958. 17p. diagrs. (NACA TN 4230) 



AN APPROXIMATE ANALYTICAL METHOD FOR 
STUDYING ENTRY INTO PLANETARY ATMOS- 
PHERES. Dean R. Chapman. May 1958. (i), lOlp. 
diagrs., tab. (NACA TN 4276) 



TURBULENCE AND TEMPERATURE FLUCTUA- 
TIONS BEHIND A HEATED GRID. R. R. Mills, Jr., 
A. L. Kistler, V. O'Brien, and S. Corrsin, Johns 
Hopkins University. Aujrust 1958. 67p. dU^rs. 
(NACA TN 4288) 



NATURAL CONVECTION INSIDE A FLAT ROTATING 
CONTAINER. Simon Ostrach and Willis H. Braun. 
September 1958. 27p. diagrs. (NACA TN 4323) 



(1.1.4.1) 
HEATING 



MEASUREMENTS OF AERODYNAMIC HEATING- 
OBTAINED DURING DEMONSTRATION FLIGHT 
TESTS OF THE DOUGLAS D-558-II AIRPLANE. 
Ira P. Jones, Jr. November 1952. 19p. diagrs., 
photo., tab. (NACA RM L52I26a) 



TESTS OF AERODYNAMICALLY HEATED MULTI- 
WEB WING STRUCTURES IN A FREE JET AT MACH 
NUMBER 2. TWO ALUMINUM-ALLOY MODELS OF 
20-INCH CHORD WITH 0.064- AND 0.081-INCH- 
THICK SKIN. George E. Griffith, Georgene H. 
Miltonberger, and Richard Rosecrans. August 1955. 
39p. diagrs., photos., tabs. (NACA RM L55F13) 



THE EFFECT OF FLUID REJECTION ON THE COM- 
PRESSIBLE TURBULENT BOUNDARY LAYER - 
PRELIMINARY TESTS ON TRANSPIRATION COOL- 
ING OF A FLAT PLATE AT M=2.7 WITH AIR AS 
THE INJECTED GAS. Morris W. Rubesin, 
Constantine C. Pappas, and Arthur F. Okuno. 
December 1955. 37p. diagrs. (NACA RM A55I19) 



THE INFLUENCE OF SURFACE INJECTION ON 
HEAT TRANSFER AND SKIN FRICTION ASSOCI- 
ATED WITH THE HIGH-SPEED TURBULENT 
BOUNDARY LAYER, Morris W. Rubesin. 
February 1956. I6p. diagrs. (NACA RM A55L13) 



THE EFFECT OF FLUID INJECTION ON THE 
COMPRESSIBLE TURBULENT BOUNDARY LAYER 
- THE EFFECT ON SKIN FRICTION OF AIR 
INJECTED INTO THE BOUNDARY LAYER OF A 
CONE AT M = 2.7. Thorval Tendeland and Arthur 
F. Okuno. June 1956. 23p. diagrs. 
(NACA RM A56D05) 



INVESTIGATION OF THE LAMINAR AERODYNAMIC 
HEAT-TRANSFER CHARACTERISTICS OF A 
HKMISPHERE-CYUNDER IN THE LANGLEY 
11 -INCH HYPERSONIC TUNNEL AT A MACH NUM- 
BER OF 6.8. Davis H. Crawford and William D. 
McCauley. 1957. ii, 21p. diagrs., photos., tab. 
(NACA Rept. 1323. Supersedes TN 3706) 



SOME EFFECTS OF HEAT TRANSFER AT MACH 
NUMBER 2.0 AT STAGNATION TEMPERATURES 
BETWEEN 2,310° AND 3,500° R ON A MAGNESIUM 
FIN WITH SEVERAL LEADING-EDGE MODIFICA- 
TIONS. William M. Bland, Jr., and Waiter E. 
Bressette. April 1957. 29p. diagrs., photos., tab. 
(NACA RM L57C14) 



FLIGHT MEASUREMENTS OF BOUNDARY-LAYER 
TEMPEKATUHE PROFILES ON A BODY OF REVO- 
LUTION (NACA RM-10) AT MACH NUMBERS FROM 
1.2 TO 3.5. Andrew G. Swanson, James J . Buglia. 
and Leo T. Chauvin. July 1957. 40p. diagrs., 
photos. (NACA TN 4061) 



THEORY OF AIRCRAFT STRUCTURAL MODELS 
SUBJECT TO AERODYNAMIC HEATING AND EX- 
TERNAL LOADS. William J. O'Sullivan, Jr. 
September 1957. 48p. (NACA TN 4115) 



A STUDY OF THE MOTION AND AERODYNAMIC 
HEATING OF MISSILES ENTERING THE EARTH'S 
ATMOSPHERE AT HIGH SUPERSONIC SPEEDS. 
H. Julian Allen and A. J. Eggers, Jr. October 
1957. 61p. diagrs, (NACA TN 4047. Supersedes 
RM A53D28) 



MOTION OF A BALLISTIC MISSILE ANGULARLY 
MISALINED WITH THE FLIGHT PATH UPON EN- 
TERING THE ATMOSPHERE AND ITS EFFECT UP- 
ON AERODYNAMIC HEATING, AERODYNAMIC 
LOADS, AND MISS DISTANCE. H. Julian Allen. 
October 1957. 66p. diagrs., tabs. (NACA TN 4048. 
Supersedes RM ASbr'lb) 



THE USEFUL HEAT CAPACITY OF SEVERAL 
MATERIALS FOR BALLISTIC NOSE-CONE 
CONSTRUCTION. Jackson R. Stalder. 
November 1957. 19p. diagrs. {NACA TN 4141) 



APPROXIMATE CALCULATION OF THE COMPRES 
SIBLE TURBULENT BOUNDARY LAYER WITH 
HEAT TRANSFER AND ARBITRARY PRESSURE 
GRADIENT. Eh Reshotko and Maurice Tucker. 
December 1957. 34p. diagrs. (NACA TN 4154) 



EFFECTIVENESS OF VARIOUS PROTECTIVE 
COVERINGS ON MAGNESIUM FINS AT MACH NUM- 
BER 2.0 AND STAGNATION TEMPERATUF.FS U* 
TO 3,600° R. William M. Bland, Jr. January l'a^ 
48p. diagrs., photos., tab. (NACA RM L57JJ7) 



A COMPARISON OF TWO METHODS FOR CALCU- 
LATING TRANSIENT TEMPERATURES FOR THICK 
WALLS. James J. Bugiia and Helen Brinkwcrth. 
August 1958. 1 9p. diagrs., tab. (NACA TN 4343) 



A MACH 4 ROCKET-POWERED SUPERSONIC TUN- 
NEL USING AMMONIA -OXYGEN AS WORKING 

FLUID. Robert W. Graham, Eleanor Costilow 
Guentert, and Vearl N. Huff. September 1958. 53p. 
diagrs., photos. (NACA TN 4325) 



HEAT TRANSr'ER AND THERMAL STRFSSES IN 
SANDWICH PANELS. Robert!. Swann. Septemov 
1958. 34p. diagrs., tabs. (NACA TN 4349) 



TABLES AND GRAPHS OF NORMAL-SHOCK PARAM- 
ETERS AT HYPERSONIC MACH NUMBSRS AND 
SELECTED ALTITUDES. Paul W. Huber. September 
1958. 26p. diagrs., :.abs (NACA TN 4352} 



22 



(1) AERODYNAMICS 



(1.1.4.2) 

HEAT TRANSFER 



NACA INVESTIGATIONS OF ICING-PROTECTION 
SYSTEMS FOR TURBOJET -ENGINE INSTALLA- 
TIONS. Uwe von Glahn, Edmund E. Callaghan, and 
Vernon H. Gray. May 2, 1951. (ii), 83p. diagrs., 
photos. (NACA RM E51B12) 



INVESTIGATION OF WATER-SPRAY COOLING OF 
TURBINE BLADES IN A TURBOJET ENGINE. 
John C. Frethe and wiiiiam J. Steiptlug. March 
1953. 45p. diagrs., photos., tab. 
(NACA RM E53A23) 



EXPLORATORY INVESTIGATION OF TRANSPIRA- 
TION COOLING TO ALLKVIATE AERODYNAMIC 
HEATING ON AN 8" CONE IN A FREE JET AT A ^ 
MACH NUMBER OF 2.05. William J . O'Sullivan, 
Leo T. Chauvin, and Charles R. Rumsey. September 
1953. 2tip. diagrs., photos. (NACA RM L53H06) 



EXPERIMENTAL INVESTIGATION OF SEVERAL 
WATER-INJECTION CONFIGURATIONS FOR 
TURBINE-BLADE SPRAY COOLING IN A TURBOJET 
ENGINE. John C. Freche and Roy A. McKinnon. 
October 1953. 37p. photos., diagrs., tabs. 
(NACA RM E53H06) 



PRELIMINARY INVESTIGATION OF PUMPING AND 
THRUST CHARACTERISTICS OF FULL-SIZE 
COOLING-AIR EJECTORS AT SEVERAL EXHAUST- 
GAS TEMPERATURES. W. K. Greathouse. April 
1954. 130p. diagrs., photos., tab, 
(NACA RM E54A18) 



COOLING CHARACTERISTICS OF A 
TRANSPIRATION -COOLED AFTERBURNER WITH A 
POROUS WALL OF BRAZED AND ROLLED WIRE 
CLOTH. William K. Koffel. August 1954. 68p. 
diagrs., photos., tabs. (NACA RM E54E25) 



INVESTIGATION OF POROUS GAS-HEATED 
LEADING-EDGE SECTION FOR ICING PROTECTION 
OF A DELTA WING. Dean T. Bowden. January 
1955. 54p. diagrs., photos., tab. 
(NACA RM E54I03) 



EXPLORATORY TESTS OF TRANSPIRATION COOL- 
ING OF A POROUS 8° CONE AT M = 2.05 USING 
NITROGEN GAS, HELIUM GAS, AND WATER AS 
THE COOLANTS. Leo T. Chauvin and Howard S. 
Carter. June 1955. 22p. diagrs., photos., tab. 
(NACA RM L55C29) 



THE EFFECT OF FLUID INJECTION ON THE COM- 
PRESSIBLE TURBULENT BOUNDARY LAYER - 
PRELIMINARY TESTS ON TRANSPIRATION COOL- 
ING OF A FLAT PLATE AT M = 2.7 WITH AIR AS 
THE INJECTED GAS. Morris W. Rubesin, 
Constantine C. Pappas, and Arthur F. Okuno. 
December 1955. 37p. diagrs. (NACA RM A55I19) 



THE INFLUENCE OF SURFACE REJECTION ON 
HEAT TRANSFER AND SKIN FRICTION ASSOCI- 
ATED WITH THE HIGH-SPEED TURBULENT 
BOUNDARY LAYER. Morris W. Rubesin. 
February 1956. 16p. diagrs. (NACA RM A55L13) 



EFFECT OF MACH NUMBER ON BOUNDARY - 
LAYER TRANSITION IN THE PRESENCE OF PRES- 
SURE RISE AND SURFACE ROUGHNESS ON AN 
OGIVE-CYLINDER BODY WITH COLD WALL 
CONDITIONS. Robert J. Carros. April 1956. 
30p. diagrs., photos. (NACA RM A56B15) 



HEAT REQUIREMENTS FOR ICE PROTECTION OF 
A CYCLICALLY GAS-HEATED, 36° SWEPT AIR- 
FOIL WITH PART IAL-SPAN LEADING-EDGE SLAT. 
Vernon H. Gray and Uwe H. von Glahn. May 1956. 
73p. diagrs., photos., tabs. (NACA RM E56B23) 



THE EFFECT OF FLUID INJECTION ON THE 
COMPRESSIBLE TURBULENT BOUNDARY LAYER 
- THE EFFECT ON SKIN FRICTION OF AIR 
INJECTED INTO THE BOUNDARY LAYER OF A 
CONE AT M = 2.7. Thorval Tendeland and Arthur 
F. Okuno. June 1956. 23p. diagrs. 
(NACA RM A56D05) 



INVESTIGATION OF THE LAMINAR AERODYNAMIC 
HEAT -TRANSFER CHARACTERISTICS OF A 
HEMISPHERE-CYLINDER IN THE LANGLEY 
11-INCH HYPERSONIC TUNNEL AT A MACH NUM- 
BER OF 6.8. Davis H. Crawford and William D. 
McCauley. 1957. ii, 21p. diagrs., photos., tab. 
(NACA Rept. 1323. Supersedes TN 3706) 



AVERAGE PROPERTIES OF COMPRESSIBLE LAM- 
INAR BOUNDARY LAYER ON FLAT PLATE WITH 
UNSTEADY FLIGHT VELOCITY. Franklin K. 
Moore and Simon Ostrach. 1957. ill, 12p. diagrs., 
tabs. (NACA Rept. 1325. Supersedes TN 3886) 



SOME EFFECTS OF HEAT TRANSFER AT MACH 
NUMBER 2.0 AT STAGNATION TEMPERATURES 
BETWEEN 2,310° AND 3,500° R ON A MAGNESIUM 
FIN WITH SEVERAL LEADING-EDGE MODIFICA- 
TIONS. William M. Bland, Jr., and Walter E. 
Bressette. April 1957. 29p. diagr*., photos., tab. 
(NACA RM L57C14) 



FUGHT MEASUREMENTS OF BOUNDARY-LAYER 
TEMPERATURE PROFILES ON A BODY OF REVO- 
LUTION (NACA RM-10) AT MACH NUMBERS FROM 
1.2 TO 3.5. Andrew G. Swanson, James J. Buglia, 
and Leo T. Chauvin. July 1957. 40p. diagrs., 
photos. (NACA TN 4061) 



INFLUENCE OF TURBULENCE ON TRANSFER OF 
HEAT FROM CYLINDERS. J. Kestin and P. F. 
Maeder, Brown University. October 1957. 78p. 
diagrs., tabs. (NACA TN 4018) 



EXPERIMENTAL INVESTIGATION OF TRANSPIRA- 
TION COOLING FOR A TURBULENT BOUNDARY 
LAYER IN SUBSONIC FLOW USING AIR AS A 
COOLANT. William E. Brunk. October 1957. 
35p. diagrs. (NACA TN 4091) 



INVESTIGATION OF HEAT TRANSFER FROM A 
STATIONARY AND ROTATING CONICAL FORE- 
BODY. Robert S. Ruggeri and James P. Lewis 
October 1957. 30p. diagrs., photo., tab. 
(NACA TN 4093) 



(1) AERODYNAMICS 



23 



EFFECTS OF EXTREME SURFACE COOLING ON 
BOUNDARY-LAYER TRANSITION. John R. Jack, 
Richard J. Wisniewski, auuN. 3. Diaconis. 
(Presented at Symposium on High-Speed Aerodynam- 
ics and Structures, Gainesville, Florida, 
January 22-24, 1957.) October 1957. 19p. diagrs., 
photo. (NACA TN 4094) 



HEAT TRANSFER AND BOUNDARY-LAYER TRAN- 
SITION ON TWO BLUNT BODIES AT MACH NUMBER 
3.12. N. S. Diaconis, Richard J. Wisniewski, and 
John R. Jack. October 1957. 31p. diagrs., photo. 
(NACA TN 4099) 



THEORY AND APPARATUS FOR MEASUREMENT 
OF EMISSIVTTY FOR RADIATIVE COOLING OF 
HYPERSONIC AIRCRAFT WITH DATA FOR INCONEL 
AND INCONEL X. William J. O'Sullivan, Jr., and 
William R. Wade. October 1957. ii, 43p. 
diagrs., photos. (NACA TN 4121) 



HEAT TRANSFER AND RECOVERY TEMPER- 
ATURES ON A SPHERE WITH LAMINAR, TRAN- 
SITIONAL, AND TURBULENT BOUNDARY 
LAYERS AT MACH NUMBERS OF 2.00 AND 4.15. 
Ivan E. Beckwith and James J. Gallagher. 
December 1957. 59p. diagrs., photos. 
(NACA TN 4125) 



EFFECTS OF LEADING-EDGE BLUNTING ON THE 
LOCAL HEAT TRANSFER AND PRESSURE DISTRI- 
BUTIONS OVER FLAT PLATES IN SUPERSONIC 
FLOW. Marcus O. Creager. December 1957. 
54p. diagrs., tabs. (NACA TN 4142) 



LAMINAR BOUNDARY LAYER WITH HEAT TRANS- 
FER ON A CONE AT ANGLE OF ATTACK IN A 
SUPERSONIC STREAM. Eli Reshotko. December 
1957. (i), 64p. diagrs., tabs. (NACA TN 4152) 



ON FLOW OF ELECTRICALLY CONDUCTING 
FLUIDS OVER A FLAT PLATE IN THE PRESENCE 
OF A TRANSVERSE MAGNETIC FIELD. Vernon J. 
Rossow. 1958. ii, 20p. diagrs., tabs. 
(NACA Rept. 1358. Supersedes TN 3971) 



EFFECTIVENESS OF VARIOUS PROTECTIVE 
COVERINGS ON MAGNESIUM FINS AT MACH NUM- 
BER 2.0 AND STAGNATION TEMPERATURES UP 
TO 3,600<> R. William M. Bland, Jr. January 1958. 
48p. diagrs., photos., tab. (NACA RM L57J17) 



EVAPORATION, HEAT TRANSFER, AND VELOC- 
ITY DISTRIBUTION IN TWO-DIMENSIONAL AND 
ROTATIONALLY SYMMETRICAL LAMINAR 
BOUNDARY-LAYER FLOW. (Verdunstung, 
Warmeubergang und Geschwindigkeitsverteilung be! 
zweidimensionaler und rotationssymmetrischer 
laminarer Grenzschichtstromung. ) Nils Frossling. 
February 1958. 37p. tabs. (NACA TM 1432. 
Translation from Lunds Universitets Arsskrift, 
v. 36, no. 4. Kungl. Fysiografiska Sallskapets 
Handlingar, v. 51, no. 4, 1940) 



AN ANALYSIS OF THE TURBULENT BOUNDARY - 
LAYER CHARACTERISTICS ON A FLAT PLATE 
WITH DISTRIBUTED LIGHT -GAS INJECTION- 
Morris W. Rubesin and Constantine C. Pappas. 
February 1958. 43p. diagrs. (NACA TN 4149) 



RECOVERY TEMPERATURES AND HEAT TRANS- 
FER NEAR TWO-DIMENSIONAL ROUGHNESS 
ELEMENTS AT MACH 3.1. Paul F. Brinich. 
February 1958. 20p. diagrs. (NACA TN 4213) 



CORRELATION OF TURBULENT HEAT TRANSFER 
IN A TUBE FOR THE DISSOCIATING SYSTEM 
N204**2N02. Richard S. Brokaw. March 1958. 
17p. diagrs., tabs. (NACA RM E57K19a) 



EFFECT OF DISTRIBUTED GRANULAR-TYPE 
ROUGHNESS ON BOUNDARY-LAYER TRANSITION 
AT SUPERSONIC SPEEDS WITH AND WITHOUT SUR- 
FACE COOLING. Albert L. Braslow. March 
1958. 22p. diagrs., photos. (NACA RM L58A17) 



APPROXIMATIONS FOR THE THERMODYNAMIC 
AND TRANSPORT PROPERTIES OF HIGH- 
TEMPERATURE AIR. C Frederick Hansen. 
March 1958. 67p. diagrs., tabs. (NACA TN 4150) 



EFFECT OF WALL COOLING ON INLET PARAME- 
TERS OF A SCOOP OPERATING IN A TURBULENT 
BOUNDARY LAYER ON A FLAT OR CONICAL SUR- 
FACE FOR MACH NUMBERS 2 TO 10. Andrew Beke. 
March 1958. 21p. diagrs., tabs. 
(NACA TN 4153) 



FREE CONVECTION UNDER THE CONDITIONS OF 
THE INTERNAL PROBLEM. (Svobodnaya convectzia 
v ousloviakh vnoutrennei zadachi.) G. A. Ostroumov. 
April 1958. vii, 233p. diagrs., photos., tabs. 
(NACA TM 1407. Translation of Russian Book, 1952) 



STAGNATION-POINT HEAT TRANSFER TO BLUNT 
SHAPES IN HYPERSONIC FLIGHT, INCLUDING 
EFFECTS OF YAW. A. J. Eggers, Jr., 
C. Frederick Hansen, and Bernard E. Cunningham. 
April 1958. 54p. diagr. (NACA TN 4229) 



EFFECTS OF MACH NUMBER AND WALL- 
TEMPERATURE RATIO ON TURBULENT HEAT 
TRANSFER AT MACH NUMBERS FROM 3 TO 5. 
Thorval Tendeland. April 1958. 46p. diagrs. 
(NACA TN 4236) 



ANALYSIS OF TURBULENT FLOW AND HEAT 
TRANSFER ON A FLAT PLATE AT HIGH MACH 
NUMBERS WITH VARIABLE FLUID PROPERTIES. 
R. G. Deissler and A. L. Loeffler, Jr. April 
1958. 61p. diagrs. (NACA TN 4262) 



SUMMARY OF EXPERIMENTAL HEAT-TRANSFER 
MEASUREMENTS IN TURBULENT FLOW FOR A 
MACH NUMBER RANGE FROM 0.87 TO 5.05. 
Maurice J. Brevoort and Barbara D. Arabian. May 
1958. 43p. diagrs., photos., tab. (NACA TN 4248) 



HEAT TRANSFER IN ISOTROPIC TURBULENCE 
DURING THE FINAL PERIOD OF DECAY. D. W. 
Dunn and W. H. Reid, Johns Hopkins University 
and Ballistic Research Laboratories, U. S. Army. 
June 1958. 68p. diagrs., tabs. (NACA TN 4186) 



24 



(1) AERODYNAMICS 



ON PAIRS OF SOLUTIONS OF A CLASS OF INTER- 
NAL VISCOUS FLOW PROBLEMS WITH BODY 
FORCES. Simon Ostrach and Lynn U. Albers. 
June 1958. 2lp. diagrs., tabs. (NACA TN 4273) 



PRANDTL NUMBER EFFECTS ON UNSTEADY 
FORCED -CONVECTION HEAT TRANSFER. E. M. 
Sparrow and J. L. Gregg. June 1958. 14p. diagrs., 
tab. (NACATN4311) 



HEAT-TRANSFER AND PRESSURE MEASUREMENTS 
ON FLAT-FACED CYLINDERS AT A MACH NUMBER 
OF 2. William E. Stoney, Jr., and J . Thomas 
Markley. July 1958. 38p. diagrs,, photos., tab. 
(NACA TN 4300) 



EFFECTS OF BOUNDARY-LAYER DISPLACEMENT 
AND LEADING-EDGE BLUNTNESS ON PRESSURE 
DISTRIBUTION, SKIN FRICTION, AND HEAT TRANS- 
FER OF BODIES AT HYPERSONIC SPEEDS. 
Mitchel H. Bertram and Arthur Henderson, Jr. 
July iy;>8. 33p. diagrs. (NACA TN 4301) 



A REVIEW OF THE THERMODYNAMIC, TRANS- 
PORT, AND CHEMICAL REACTION RATE PROP- 
ERTIES OF HIGH-TEMPERATURE AIR. 
C. Frederick Hansen and Steve P. Heims. July 1958. 
33p. diagrs. (NACA TN 4359) 



COMPRESSIBLE LAMINAR FLOW AND HEAT 
TRANSFER ABOUT A ROTATING ISOTHERMAL 
DISK. Simon Ostrach and Philip R. Thornton. 
August 1958. 18p. diagrs., tab. (NACA TN 4320> 



MEASUREMENTS IN A SHOCK TUBE OF HEAT- 
TRANSFER RATES AT THE STAGNATION POINT 
OF A 1.0-INCH-DIAMETER SPHERE FOR REAL- 
GAS TEMPERATURES UP TO 7,900° R. Alexander 
P. Sabol. August 1958. 15p. diagrs., photos., tab. 
(NACA TN 4354) 



THE EFFECT OF FREE-STREAM TURBULENCE 
ON HEAT TRANSFER FROM A FLAT PLATE. 
(Shurytfbu midare ga heiban nets udentatsu nl oyobosu 
likyo ni tsuite.) Sugao Sugawara, Takashi Sato, 
Hiroyasu Komatsu, and Hiroichi Osaka. September 
1958. 21p. diagrs. (NACA TM 1441. Translation 
from Journal of Japan Society of Mechanical 
Engineering, v. 19, no. 18, 1953, p. 18-25) 



TRANSIENT TEMPERATURE DISTRIBUTION IN A 
TWO -COMPONENT SEMI-INFINITE COMPOSI'I E 
SLAB OF ARBITRARY MATERIALS SUBJECTED T^ 
AERODYNAMIC HEATING WITH A DISCONTINUOU > 
CHANGE IN EQUILIBRIUM TEMPERATURE OR 
HEAT -TRANSFER COEFFICIENT. Robert L. 
Trimpi and Robert A. Jones. September 1958. 83p. 
diagrs., tabs. (NACA TN 4308) 



ON FULLY DEVELOPED CHANNEL FLOWS: SOME 
SOLUTIONS AND LIMITATIONS, AND EFFECTS OF 
COMPRESSIBILITY, VARIABLE PROPERTIES, 
AND BODY FORCES. Stephen H. Maslen. September 
1958. 46p. diagrs., tabs. (NACA TN 4319) 



A MACH 4 ROCKET-POWERED SUPERSONIC TUN- 
NEL USING AMMONIA-OXYGEN AS WORKING 
FLUID. Robert W. Graham, Eleanor Costilow 
Guentert, and Vearl N. Huff. September 1958. 53p. 
diagrs., photos. (NACA TN 4325) 



EFFECT OF SOME EXTERNAL CROSSWISE STIFF- 
ENERS ON THE HEAT TRANSFER AND PRESSURE 
DISTRIBUTION ON A FLAT PLATE AT MACH NUM- 
BERS OF 0.77, 1.39, AND 1.98. Howard S. Carter. 
September 1958. 21p. diagrs., photo., tab. 
(NACA TN 4333) 



SIMILAR SOLUTIONS FOR THE COMPRESSIBLE 
BOUNDARY LAYER ON A YAWED CYLINDER WITH 
TRANSPIRATION COOLING. Ivan E. Beckwith. 
September 1958. 72p. diagrs., tabs. 
(NACA TN 4345) 



A NONLINEAR THEORY FOR PREDICTING THE 
EFFECTS OF UNSTEADY LAMINAR, TURBULENT, 
OR TRANSITIONAL BOUNDARY LAYERS ON THE 
ATTENUATION OF SHOCK WAVES IN A SHOCK 
TUBE WITH EXPERIMENTAL COMPARISON. 
Robert L. Trimpi and Nathaniel B. Cohen. September 
1958. 105p. diagrs., photos., tab. (NACA TN 4347) 



AN INVESTIGATION OF SUPERSONIC TURBULENT 
BOUNDARY LAYERS ON SLENDER BODIES OF 
REVOLUTION IN FREE FLIGHT BY USE OF A 
MACH-ZEHNDER INTERFEROMETER AND SHADOW- 
GRAPHS. Alvin Seiff and Barbara J. Short. 
September 1958. 57p. diagrs., photos. 
(NACA TN 4364) 



SLIP-FLOW HEAT TRANSFER FROM CYLINDERS 
IN SUBSONIC AIRSTREAMS. Lionel V. Baldwin. 
September 1958. (i), 77p. diagrs., photos., tabs^ 
(NACA TN 4369) 



ANALYTICAL AND EXPERIMENTAL INVESTIGA- 
TION OF TEMPERATURE RECOVERY FACTORS 
FOR FULLY DEVELOPED FLOW OF AIR IN A 
TUBE. R. G. Deissler, W. F. Weiland, and W. H. 
Lowdermilk. September 1958. 35p. diagrs., tab. 
(NACA TN 4376) 



PRELIMINARY HEAT -TRANSFER STUDIES ON TWO 
BODIES OF REVOLUTION AT ANGLE OF ATTACK 
AT A MACH NUMBER OF 3.12. Norman Sands and 
John R. Jack. September 1958. 29p. diagrs., 
photos., tabs. (NACA TN 4378) 



APPROXIMATE METHOD FOR CALCULATION OF 
LAMINAR BOUNDARY LAYER WITH HEAT TRANS- 
FER ON A CONE AT LARGE ANGLE OF ATTACK 
IN SUPERSONIC FLOW. William E. Brunk. 

September 1958. 26p. diagrs., tab. (NACA TN 4380) 



INVESTIGATION OF BOILING BURNOUT AND FLOW 
STABILITY FOR WATER FLOWING IN TUBES. 
Warren H. Lowdermilk, Chester D. Lanzo, and 
Byron L. Siegel, September 1958. 51p. diagrs., 
tabs. (NACA TN 4382) 



MASS TRANSFER COOLING NEAR THE STAGNATION 
POINT. Leonard Roberts. September 1958. 42p. 
diagrs. (NACA TN 4391) 



A THEORETICAL STUDY OF STAGNATION-POINT 
ABLATION. Leonard Roberts. September 1958. 
29p. diagrs. (NACA TN 4392) 



( 1 ) AERODYNAMICS 



25 



(1.1.4.3) 
ADDITIONS OF HEAT 



COMBUSTION OF ALUMINUM BOROHYDRIDE IN A 
SUPERSONIC WIND TUNNEL. Edward A. Fletcher, 
Robert G. Dorsch, and Melvin Gerstein. June 1955. 
72p. diagrs., photos., tabs. (NACA RM E55D07a) 



AN ANALYSIS OF RAM -JET -ENGINE TIME DELAY 
FOLLOWING A FUEL-FLOW DISTURBANCE. 
Fred A. Wilcox and Arthur R. Anderson. June 1955. 
38p. diagrs., tabs. (NACA RM E55D22) 



A PRELIMINARY INVESTIGATION OF STATIC- 
PRESSURE CHANGES ASSOCIATED WITH COMBUS- 
TION OF ALUMINUM BOROHYDRIDE IN A SUPER- 
SONIC WIND TUNNEL. Robert G. Dorsch, John S. 
Serafini, and Edward A. Fletcher. August 1955. 
12p. diagrs., ph-tos. (NACA RM E55F07) 



HIGH-TEMPERATURE OXIDATION AND IGNITION 
OF METALS. Paul R. Hill, David Adamson, 
Douglas H. Foland, and Walter E. Bressette. 
March 1956. 12p. diagrs. (NACA RM L55L23b) 



INVESTIGATION OF THE LAMINAR AERODYNAMIC 
HEAT -TRANSFER CHARACTERISTICS OF A 
HEMISPHERE-CYLINDER IN THE LANGLEY 
11 -INCH HYPERSONIC TUNNEL AT A MACH NUM- 
BER OF 6.8. Davis H. Crawford and William D. 
McCauley. 1957. ii, 21p. diagrs., photos., tab. 
(NACA Rept. 1323. Supersedes TN 3706) 



ATTENUATION IN A SHOCK TUBE DUE TO 
UNSTEADY-BOUNDARY -LAYER ACTION. Harold 
Mirels. 1957. iii, 19p. diagrs., tab. 
(NACA Rept. 1333. Supersedes TN 3278) 



EXPLORATORY INVESTIGATION OF AERODYNAM- 
IC EFFECTS OF EXTERNAL COMBUSTION OF 
ALUMINUM BOROHYDRIDE IN AIRSTREAM ADJA- 
CENT TO FLAT PLATE IN MACH 2.46 TUNNEL. 
Robert G. Dorsch, JohnS. Serafini, and Edward A. 
Fletcher July 1957. 91p. diagrs., photos., tabs. 
(NACA RM E57E16) 



EXPLORATORY INVESTIGATION OF STATIC- AND 
BASE -PRESSURE INCREASES RESULTING FROM 
COMBUSTION OF ALUMINUM BOROHYDRIDE 
ADJACENT TO BODY OF REVOLUTION IN SUPER- 
SONIC WIND TUNNEL. John S. Serafini, Robert G. 
Dorsch, and Edward A. Fletcher. October 1957. 
49p. diagrs., photos., tabs. (NACA RM E57E15) 



STUDY OF SOME BURNER CROSS-SECTION 
CHANGES THAT INCREASE SPACE-HEATING 
RATES Donald R. Boldman and Perry L. 
Blackshear, Jr. November 1957. 38p. diagrs., 
photos... tab. (NACA TN 4162) 



PRELIMINARY SURVEY OF PROPULSION USING 
CHEMICAL ENERGY STORED IN THE UPPER 
ATMOSPHERE. Lionel V. Baldwin and Perry L. 
Blackshear. Appendix D: HEAT TRANSFER AND 
FRICTION DRAG. James F. Schmidt. May 1958. 
73p. diagrs., tabs. (NACA TN 4267) 



A PERFORMANCE ANALYSIS OF METHODS FOR 
HANDLING EXCESS INLET FLOW AT SUPERSONIC 
SPEEDS. Donald P. Hearth and James F. Connors. 
May 1958. 26p. diagrs., tab. (NACA TN 4270) 



PRANDTL NUMBER EFFECTS ON UNSTEADY 
FORCED-CONVECTION HEAT TRANSFER. E. M. 
Sparrow and J. L. Gregg. June 1958. 14 p. diagrs., 
tab. (NACA TN 4311) 



INVESTIGATION OF BOILING BURNOUT AND FLOW 
STABILITY FOR WATER FLOWING IN TUBES. 
Warren H. Lowdermilk, Chester D. Lanzo, and 
Byron L. Siegel. September 1958. 51p. diagrs., 
tabs. (NACA TN 4382) 



AN ANALYSIS OF RAMJET ENGINES USING SUPER- 
SONIC COMBUSTION. Richard J. Weber and John 
S. MacKay. September 1958. 49p. diagrs., tab. 
(NACA TN 4386) 



(1.1.5) 
FLOW OF RAREFIED OASES 



APPROXIMATIONS FOR THE THERMODYNAMIC 
AND TRANSPORT PROPERTIES OF HIGH- 
TEMPERATURE AIR. C. Frederick Hansen. 
March 1958. 67p. diagrs., tabs. (NACA TN 4150) 



PRELIMINARY SURVEY OF PROPULSION USING 
CHEMICAL ENERGY STORED IN THE UPPER 
ATMOSPHERE. Lionel V. Baldwin and Perry L. 
Blackshear. Appendix D: HEAT TRANSFER AND 
FRICTION DRAG. James F. Schmidt. May 1958. 
73p. diagrs., tabs. (NACA TN 4267) 



A REVIEW OF THE THERMODYNAMIC, TRANS- 
PORT, AND CHEMICAL REACTION RATE PROP- 
ERTIES OF HIGH-TEMPERATURE AIR. 
C. Frederick Hansen and Steve P. Helms. July 1958. 
33p. diagrs. (NACA TN 4359) 



(1.1.5.1) 
SLIP FLOW 



SLD?-FLOW HEAT TRANSFER FROM CYLINDERS 
IN SUBSONIC AIRSTREAMS. Lionel V. Baldwin. 
September 1958. (i), 77p. diagrs., photos., tabs. 
(NACA TN 4369) 



(1.1.5.2) 

FREE MOLECULE FLOW 



LAG IN PRESSURE SYSTEMS AT EXTREMELY LOW 
PRESSURES. William T. Davis. September 1958. 
16p. diagrs. (NACA TN 4334) 



26 



(1) AERODYNAMICS 



SLIP-FLOW HEAT TRANSFER FROM CYLINDERS 
IN SUBSONIC AIRSTREAMS. Lionel V. Baldwin. 
September 1958. (I), 77p. diagrs., photos., tabs. 
(NACA TN 4369) 



(U.6) 
TIME - DEPENDENT FLOW 



EFFECTS OF THERMAL RELAXATION_AND ^ 
SPECIFIC-HEAT CHANGES ON MnASlmEMENiS 
WITH A PNEUMATIC -PROBE PYROMETER. P. W. 
Kuhns. July 1957. (ii), 67p. diagrs., tabs. 
(NACA TN 4026) 



EXPERIMENTAL INVESTIGATION OF ATTENUA- 
TION OF STRONG SHOCK WAVES IN A SHOCK 
TUBE WITH HYDROGEN AND HELIUM AS DRIVER 
GASES. Jim J, Jones. July 1957. 24p. diagrs., 
"hoto. (NACA TN 4072) 



WIND-TUNNEL INVESTIGATION OF EFFECTS OF 
GROUND PROXIMITY AND OF SPLIT FLAPS ON 
THE LATERAL STABILITY DERIVATIVES OF A 60° 
DELTA-WING MODEL OSCILLATING IN YAW. 
Byron M. Jaquet. September 1957. 32p. diagrs. 
photos., tab. (NACA TN 4119) 



AN EXPERIMENTAL STUDY OF THE TURBULENT 
BOUNDARY LAYER ON A SHOCK-TUBE WALL. 
Paul B. Go ode ram June 1958. 63p. diagrs., 
photos., tab. (NACA TN 4243) 



REFLECTION AND TRANSMISSION OF SOUND BY A 
SLOTTED WALL SEPARATING TWO MOVING FLUID 
STREAMS. Raymond L. Barger. June 1958. 14p. 
diagrs. (NACA TN 4295) 



TRANSIENT TEMPERATURE DISTRIBUTION IN A 
TWO-COMPONENT SEMI-INFINITE COMPOSH L 
SLAB OF ARBITRARY MATERIALS SUBJECTED TO 
AERODYNAMIC HEATING WITH A DISCONTINUOUS 
CHANGE IN EQUILIBRIUM TEMPERATURE OR 
HEAT -TRANSFER COEFFICIENT. Robert L. 
Trimpi and Robert A. Jones. September 1958 83p. 
diagrs., tabs. (NACA TN 4308) 



A NONLINEAR THEORY FOR PREDICTING THE 
EFFECTS OF UNSTEADY LAMINAR, TURBULENT, 
OR TRANSITIONAL BOUNDARY LAYERS ON THE 
ATTENUATION OF SHOCK WAVES IN A SHOCK 
TUBE WITH EXPERIMENTAL COMPARISON. 
Robert L. Trimpi and Nathaniel B- Cohen. September 
1958. 105p. diagrs., photos., tab. (NACA TN 4347) 



(1) AERODYNAMICS 



27 



(1.2) 
Wings 



INVESTIGATION OF THE AERODYNAMIC CHARAC- 
TERISTICS AT HIGH SUPERSONIC MACH NUMBERS 
OF A FAMILY OF DELTA WINGS HAVING DOUBLE- 
WEDGE SECTIONS WITH THE MAXIMUM THICK- 
NESS AT 0.18 CHORD. Mitchel H. Bertram and 
William D. McCauley. October 1954. 54p. diagrs., 
photos., tabs. (NACA RM L54G28) 



(IAD 
WINOMCnOMS 



WING LOADS AND LOAD DISTRIBUTIONS THROUGH- 
OUT THE LIFT RANGE OF THE DOUGLAS X- 3 
RESEARCH AIRPLANE AT TRANSONIC SPEEDS. 
Earl R. Keener and Gareth H. Jordan. November 
1956. 191p. diagrs., photo., tabs. 
(NACA RM H56G13) 



(1.2.1.1) 
SECTION THEORY 



LOAD DISTRIBUTIONS ASSOCIATED WITH CON- 
TROLS AT SUPERSONIC SPEEDS- K. R. Czamecki 
and Douglas R. Lord. Mav 1953. 21p. photo., 
diagrs. (NACA RM L53D15a) 



THEORETICAL DETERMINATION OF LOW-DRAG 
SUPERCAVTTATING HYDROFOILS AND THEIR 
TWO-DIMENSIONAL CHARACTERISTICS AT ZERO 
CAVITATION NUMBER. Virgil E. Johnson, Jr. 
September 1957. 29p. diagrs. (NACA RM L57Glla) 



A RAPID METHOD FOR PREDICTING ATTACHED- 
SHOCK SHAPE. Eugene S. Love and Ronald H. 
Long. October 1957. 34p. diagrs., tab. 
(NACA TN 4167) 



THEORETICAL AND EXPERIMENTAL INVESTIGA- 
TION OF ARBITRARY ASPECT RATIO, SUPER- 
CAVITATING HYDROFOILS OPERATING NEAR THE 
FREE WATER SURFACE. Virgil E. Johnson, Jr. 
December 1957. 94p. diagrs., photos. 
(NACA RML57I16) 



A REEXAMINATION OF THE USE OF SIMPLE 
CONCEPTS FOR PREDICTING THE SHAPE AND 
LOCATION OF DETACHED SHOCK WAVES. 
Eugene S. Love. December 1957. 53p. diagrs. 
(NACA TN 4170) 



EFFECT OF ANGLE OF ATTACK AND THICKNESS 
ON AERODYNAMIC COEFFICIENTS OF A RIGID 
WING OSCILLATING AT VERY LOW FREQUENCIES 
IN TWO-DIMENSIONAL SUPERSONIC FLOW. 
Franks. Malvestuto, Jr., and Julia M. Goodwin. 
January 1958. 65p. diagrs. (NACA TN 4069) 



THEORETICAL PRESSURE DISTRIBUTIONS FOR 
SEVERAL RELATED NONLIFTING AIRFOILS AT 
HIGH SUBSONIC SPEEDS. John R. Spreiter, 
Alberta Y. Alksne, andB. Jeanne Hyett. January 
1958. (i), 52p. diagrs., tab. (NACA TN 4148) 



ELLIPTIC FUNCTIONS AND INTEGRALS WITH 
REAL MODULUS IN FLUID MECHANICS. (Les 
Functions et Integrates Elliptiques a Module Reel en 
Mecanique des Fluides). Robert Legendre. June 
1958. 113p. diagrs^ (NACA TM 1435. Translation 
of Office National d' Etudes et de Recherches 
Aeronautiques, Publication 71, 1954) 



(1.2.1.2) 
SECTION VARIABLES 



TWO-DIMENSIONAL CHORDWISE LOAD DISTRIBU- 
TIONS AT TRANSONIC SPEEDS. Walter F. Lindsay 
and Richards. Dick. February 1952. 41p. diagrs., 
photos. (NACA RM L5U07) 



WING PRESSURE DISTRIBUTIONS AT LOW LIFT 
FOR THE XF-92A DELTA -WING AIRPLANE AT 
TRANSONIC SPEEDS. Earl R. Keener. October 
1954. 54p. diagrs., photos., tabs. 
(NACA RM H54H06) 



INVESTIGATION OF THE EFFECTS OF AN AIRFOIL 
SECTION MODIFICATION ON THE AERODYNAMIC 
CHARACTERISTICS AT SUBSONIC AND SUPERSONIC 
SPEEDS OF A THIN SWEPT WING OF ASPECT 
RATIO 3 IN COMBINATION WITH A BODY. David 
Graham and William T. Evans. June 1955. 46p. 
diagrs., tabs. (NACA RM A55D11) 



DATA FROM LARGE-SCALE LOW-SPEED TESTS 
OF AIRPLANE CONFIGURATIONS WITH A THIN 45° 
SWEPT WING INCORPORATING SEVERAL 
LEADING-EDGE CONTOUR MODIFICATIONS. 
William T. Evans. May 1956. HOp. diagrs., 
photo., tabs. (NACA RM A56B17) 



(1.2. 1.2. 1) 
Camber 



LONGITUDINAL AERODYNAMIC CHARACTERISTICS 
OF MODEL AIRPLANE CONFIGURATION EQUIPPED 
WITH A SCALED X-l AIRPLANE WING. James H. 
Parks. April 1952. 37p. diagrs. 
(NACA RM L5lL10a) 



THEORETICAL DETERMINATION OF LOW-DRAG 
SUPERCAVTTATING HYDROFOILS AND THEIR 
TWO-DIMENSIONAL CHARACTERISTICS AT ZERO 
CAVITATION NUMBER. Virgil E. Johnson, Jr. 
September 1957. 29p. diagrs. (NACA RM L57Glla) 



28 



(1) AERODYNAMICS 



THEORETICAL AND EXPERIMENTAL INVESTIGA- 
TION OF ARBITRARY ASPECT RATIO, SUPER- 
CAVITATING HYDROFOILS OPERATING NEAR THE 
FREE WATER SURFACE. Virgil E. Johnson, Jr. 
December 1957. 94p. diagrs., photos. 
(NACARML57I16). 



(1.2.1.2.2) 

Thickness 



EFFECTS OF A SERIES OF INBOARD PLAN-FORM 
MODIFICATIONS ON THE LONGITUDINAL CHAR- 
ACTERISTICS OF TWO 470 SWEPTBACK WINGS OF 
ASPECT RATIO 3.5, TAPER RATIO 0.2, AND DIF- 
FERENT THICKNESS DISTRIBUTIONS AT MACH 
NUMBERS OF 1.61 AND 2.01. Morton Cooper and 
John R. Sevier, Jr. July 1953. 43p. diagrs., 
photos., tabs. (NACA RM L53E07a) 



EFFECTS OF A SERIES OF INBOARD PLAN-FORM 
MODIFICATIONS ON THE LONGITUDINAL CHAR- 
ACTERISTICS OF TWO UNSWEPT WINGS OF AS- 
PECT RATIO 3.5, TAPER RATIO 0.2 ( AND DIF- 
FERENT THICKNESS DISTRIBUTIONS AT MACH 
NUMBERS OF 1.61 AND 2.01. JohnR. Sevier, Jr. 
February 1954. 43p. diagrs., photos. 
(NACARM L53K11) 



EXPERIMENTAL INVESTIGATION OF INTERFER- 
ENCE EFFECTS OF LATERAL -SUPPORT STRUTS 
ON AFTERBODY PRESSURES AT MACH 1.9. John 
L. Klann and Ronald G. Huff. May 1956. 13p. 
diagrs., tab. (NACA RM E56C16) 



WIND-TUNNEL INVESTIGATION OF THE EFFECTS 
OF WING THICKNESS ON THE STATIC LONGITU- 
DINAL AND LATERAL STABILITY OF UNSWEPT 
WINGS OF ASPECT RATIO 3 AT HIGH SUBSONIC 
SPEEDS. William C. Hayes, Jr., and Edward C. 
Polhamus. August 1956. 43p, diagrs., photos. 
(NACA RM L56E30a) 



INVESTIGATION OF THE EFFECTS OF PROFILE 
SHAPE ON THE AERODYNAMIC AND STRUCTURAL 
CHARACTERISTICS OF THIN, TWO-DIMENSIONAL 
AIRFOILS AT SUPERSONIC SPEEDS. Elliott D. 
Katzen, Donald M. Kuehn, and William A . Hill, Jr. 
September 1957. 59p. diagrs., tabs. 
(NACA TN 4039. Supersedes RM A54B08a) 



EFFECT OF ANGLE OF ATTACK AND THICKNESS 
ON AERODYNAMIC COEFFICIENTS OF A RIGID 
WING OSCILLATING AT VERY LOW FREQUENCIES 
IN TWO-DIMENSIONAL SUPERSONIC FLOW. 
Franks. Malvestuto, Jr., and Julia M. Goodwin. 
January 1958. 6 5p. diagrs. (NACA TN 4069) 



THEORETICAL PRESSURE DISTRIBUTIONS FOR 
SEVERAL RELATED NONLIFTING AIRFOILS AT 
HIGH SUBSONIC SPEEDS. JohnR. Spreiter, 
Alberta Y. Alksne, andB. Jeanne Hyett. January 
1958. (i), 52p. diagrs., tab. (NACA TN 4148) 



ORDINATES AND THEORETICAL PRESSURE- 
DISTRIBUTION DATA FOR NACA 6- AND 6A -SERIES 
AIRFOIL SECTIONS WITH THICKNESSES FROM 2 TO 
21 AND FROM 2 TO 15 PERCENT CHORD, RESPEC- 
TIVELY. Elizabeth W. Patterson and Albert L. 
Braslow. September 1958. 99p. diagrs. 
(NACA TN 4322) 



(1.2. 1.2.3) 
Thickness Distribution 



LOAD DISTRIBUTIONS ASSOCIATED WITH CON- 
TROLS AT SUPERSONIC SPEEDS. K. R. Czarnecki 
and Douglas R. Lord. May 1953. 21p. photo., 
diagrs. (NACA RM L53D15a) 



EFFECTS OF A SERIES OF INBOARD PLAN-FORM 
MODIFICATIONS ON THE LONGITUDmAL CHAR- 
ACTERISTICS OF TWO 470 SWEPTBACK WINGS OF 
ASPECT RATIO 3.5, TAPER RATIO 0.2, AND DIF- 
FERENT THICKNESS DISTRIBUTIONS AT MACH 
NUMBERS OF 1.61 AND 2.01. Morton Cooper and 
JohnR. Sevier, Jr. July 1953. 43p. diagrs., 
photos., tabs. {NACA RM L53E07a) 



EFFECTS OF A SERIES OF INBOARD PLAN-FORM 
MODIFICATIONS ON THE LONGITUDINAL CHAR- 
ACTERISTICS OF TWO UNSWEPT WINGS OF AS- 
PECT RATIO 3.5, TAPER RATIO 0.2, AND DIF- 
FERENT THICKNESS DISTRIBUTIONS AT MACH 
NUMBERS OF 1.81 AND 2.01. John R. Sevier, Jr. 
February 1954. 43p. diagrs., photos. 
(NACARM L53KU) 



FLOW AND FORCE CHARACTERISTICS OF 
2-PERCENT-THICK AIRFOILS AT TRANSONIC 
SPEEDS. Walter F. Lindsey and Emma Jean 
Landrum. January 1955. 74p. diagrs., photos. 
(NACA RM L54I30) 



INVESTIGATION OF UNSTEADY FLOW PAST FOUR 
NACA 6-PERCENT-THICK AIRFOIL SECTIONS. 
Charles L. Ladson and Walter F. Lindsey. July 
1956. 17p. diagrs. (NACA RM L56E14) 



COMPRESSIBILITY EFFECTS ON A HOVERING 
HELICOPTER ROTOR HAVING AN NACA 0018 ROOT 
AIRFOIL TAPERING TO AN NACA 0012 TIP AIR- 
FOIL. Robert D. Powell, Jr. September 1957. 
25p. diagrs. (NACA RM L57F26) 



INVESTIGATION OF THE EFFECTS OF PROFUSE 
SHAPE ON THE AERODYNAMIC AND STRUCTURAL 
CHARACTERISTICS OF THIN, TWO-DIMENSIONAL 
AIRFOILS AT SUPERSONIC SPEEDS. Elliott D. 
Katzen, Donald M. Kuehn, and William A. Hill, Jr. 
September 1957. 59p. diagrs., tabs. 
(NACA TN 4039. Supersedes RM A54B08a) 



STAGNATION-POINT HEAT TRANSFER TO BLUNT 
SHAPES IN HYPERSONIC FLIGHT, DELUDING 
EFFECTS OF YAW. A. J. Eggers, Jr., 
C. Frederick Hansen, and Bernard E. Cunningham. 
April 1958. 54p. diagr. (NACA TN 4229) 



LOW TIP MACH NUMBER STALL CHARACTERIS- 
TICS AND HIGH TIP MACH NUMBER COMPRESSI- 
BILITY EFFECTS ON A HELICOPTER ROTOR 
HAVING AN NACA 0009 TD? AIRFOIL SECTION. 
Robert D. Powell, Jr., and Paul J. Carpenter. July 
1958. 28p. diagrs. (NACA TN 4355) 



(1) AERODYNAMICS 



29 



ORDINATES AND THEORETICAL PRESSURE- 
DISTRIBUTION DATA FOR NACA 6- AND 6A -SERIES 
AIRFOIL SECTIONS WITH THICKNESSES FROM 2 TO 
21 AND FROM 2 TO 15 PERCENT CHORD, RESPEC- 
TIVELY. Elizabeth W. Patterson and Albert L. 
Braslow. September 1958. 99p. diagrs. 
(NACA TN 4322) 



EFFECTS OF COMPRESSIBILITY ON ROTOR HOV- 
ERING PERFORMANCE AND SYNTHESIZED BLADE - 
SECTION CHARACTERISTICS DERIVED FROM 
MEASURED ROTOR PERFORMANCE OF BLADES 
HAVING NACA 0015 AIRFOIL TIP SECTIONS. 
James P. Shivers and Paul J. Carpenter. September 
1958. 28p. diagrs. (NACA TN 4356) 



(1.2. 1.2.5) 
Surface Conditions 



MEASUREMENTS OF AERODYNAMIC HEATING 
OBTAINED DURING DEMONSTRATION FLIGHT 
TESTS OF THE DOUGLAS D-558-II AIRPLANE. 
Ira P. Jones, Jr. November 1952. 19p. diagrs., 
photo., tab. (NACA RM L52I26a) 



IMPINGEMENT OF CLOUD DROPLETS ON 3G.5- 
PERCENT-THICK JOUKOWSKI AIRFOIL AT ZERO 
ANGLE OF ATTACK AND DISCUSSION OF USE AS 
CLOUD MEASURING INSTRUMENT IN DYE-TRACER 
TECHNIQUE. R. J. Brun and Dorothea E. Vogt. 
September 1957. 52p. diagrs., tabs. 
(NACA TN 4035) 



INVESTIGATION OF THE EFFECTS OF PROFILE 
SHAPE ON THE AERODYNAMIC AND STRUCTURAL 
CHARACTERISTICS OF THIN, TWO-DIMENSIONAL 
AIRFOILS AT SUPERSONIC SPEEDS. Elliott D. 
Katzen, Donald M. Kuehn, and William A . Hill, Jr. 
September 1957. 59p. diagrs., tabs. 
(NACA TN 4039. Supersedes RM A54B08a) 



A THERMAL SYSTEM FOR CONTINUOUS MONI- 
TORING OF LAMINAR AND TURBULENT 
BOUNDARY-LAYER FLOWS DURING ROUTINE 
FLIGHT. Norman R. Richardson and Elmer A 
Horton. September 1957. 25p. diagrs., photos. 
(NACA TN 4108) 



A LOW-SPEED EXPERIMENTAL INVESTIGATION 
OF THE EFFECT OF A SANDPAPER TYPE OF 
ROUGHNESS ON BOUNDARY-LAYER TRANSITION. 
Albert E. von Doenhoff and Elmer A. Horton. 1958. 
ii, 16p. diagrs., photos. (NACA Rept. 1349. 
Supersedes TN 3858) 



CORRELATIONS AMONG ICE MEASUREMENTS, 
IMPINGEMENT RATES, ICING CONDITIONS, AND 
DRAG COEFFICIENTS FOR UNSWEPT NACA 65A004 
AIRFOIL. Vernon H.Gray. February 1958. 45p. 
diagrs., photos., tabs. (NACA TN 4151) 



AERODYNAMIC EFFECTS CAUSED BY ICING OF 
AN UNSWEPT NACA 65A004 AIRFOIL. Vernon H. 
Gray and Uwe H. von Glahn. February 1958. 47p. 
diagrs., photos., tabs. (NACA TN 4155) 



THE TURBULENT BOUNDARY LAYER ON A ROUGH 
CURVILINEAR SURFACE . (Turbulentnyi 
r ogranichnyi sloi na sherpokhovatoi krivolineinoi 
poverkhnosti.) V. F. Droblenkov. September 1958. 
10p. diagrs. (NACA TM 1440. Translation from 
Akademiia Nauk SSSR, Izvestiia, Otdelenie 
Tekhnicheskikh Nauk, no. 8, 1955, p. 17-21) 



SIMPLIFIED METHOD FOR DETERMINATION OF 
CRITICAL HEIGHT OF DISTRIBUTED ROUGHNESS 
PARTICLES FOR BOUNDARY-LAYER TRANSITION 
AT MACH NUMBERS FROM TO 5. Albert L. 
Braslow and Eugene C. Knox. September 1958. 
18p. diagrs., photos. (NACA TN 4363) 



(1.2. 1. 3) 
DESIGNATED PROFILES 



A STUDY OF LOCAL-PRESSURE FLUCTUATIONS 
RELATIVE TO STATIC -PRESSURE DISTRIBUTIONS 
OF TWO-DIMENSIONAL AIRFOILS AT HIGH SUB- 
SONIC MACH NUMBERS. Charles F- Coe. 
December 1955. 66p. diagrs., photos. 
(NACARM A55J11) 



INVESTIGATION OF THE EFFECTS OF PROFILE 
SHAPE ON THE AERODYNAMIC AND STRUCTURAL 
CHARACTERISTICS OF THIN, TWO-DIMENSIONAL 
AIRFOILS AT SUPERSONIC SPEEDS. Elliott D. 
Katzen, Donald M. Kuehn, and William A. Hill, Jr. 
September 1957. 59p. diagrs., tabs. 
(NACA TN 4039. Supersedes RM A54B08a) 



ORDINATES AND THEORETICAL PRESSURE- 
DISTRIBUTION DATA FOR NACA 6- AND 6A -SERIES 
AIRFOIL SECTIONS WITH THICKNESSES FROM 2 TO 
21 AND FROM 2 TO 15 PERCENT CHORD, RESPEC- 
TIVELY. Elizabeth W. Patterson and Albert L. 
Braslow. September 1958. 99p. diagrs. 
(NACA TN 4322) 



(1.2.1.4) 
HIGH-LIFT DEVICES 



ANALYSIS OF SOME PARAMETERS USED IN 
CORRELATING BLOWING-TYPE BOUNDARY- 
LAYER CONTROL DATA. Mark W. Kelly. 
Severn. er 1956. 19p. diagrs. (NACA RM A56F12) 



ESTIMATION OF INCREMENTAL PITCHING MO- 
MENTS DUE TO TRAILING -EDGE FLAPS ON 
SWEPT AND TRIANGULAR WINGS . Harry A. 
James and Lynn W. Hunton. July 1957. 31p. 
diagrs., tab. (NACA TN 4040. Supersedes 
RM A55D07) 



PRELIMINARY INVESTIGATION OF THE CHAR- 
ACTERISTICS OF A TWO-DIMENSIONAL WING AND 
PROPELLER WITH THE PROPELLER PLANE OF 
ROTATION IN THE WING -CHORD PLANE. David 
H. Hickey. August 1957. 12p. diagrs. 
(NACARMA57F03) 



30 



(1) AERODYNAMICS 



(1.2. 1.4.1) 
Plain Flaps 



LOW-SPEED CHORDWISE PRESSURE DISTRIBU- 
TIONS NEAR THE MIDSPAN STATION OF THE 
SLOTTED FLAP AND AILERON OF A 1/4 -SCALE 
MODEL OF THE BELL X-l AIRPLANE WITH A 
4-PERCENT -THICK, ASPECT-RATIO-4, UNSWEPT 
WING. William C. Moseley, Jr., and Robert T-. 
Taylor. March 1954. 59p. diagrs., photos., tabs. 
(NACA RM L&3L1B) 



THE EFFECTS OF BLOWING OVER VARIOUS 
TRAILING-EDGE FLAPS ON AN NACA 0006 AIR- 
FOIL SECTION, COMPARISONS WITH VARIOUS 
TYPES OF FLAPS ON OTHER AIRFOIL SECTIONS, 
AND AN ANALYSIS OF FLOW AND POWER RELA- 
TIONSHD7S FOR BLOWING SYSTEMS. Jules B. 
Dods, Jr., and Earl C. Watson. June 1956. 145p. 
diagrs., photos., tab. (NACA RM A56C01) 



ESTIMATION OF INCREMENTAL PITCHING MO- 
MENTS DUE TO TRAILING-EDGE FLAPS ON 
SWEPT AND TRIANGULAR WINGS. Harry A. 
James and Lynn W. Hunton. July 1957. 31p. 
diagrs., tab. (NACA TN 4040. Supersedes 
RM A55D07) 



(1.2.1.4.2) 
Split Flaps 



ESTIMATION OF INCREMENTAL PITCHING MO- 
MENTS DUE TO TRAILING-EDGE FLAPS ON 
SWEPT AND TRIANGULAR WINGS. Harry A. 
James and Lynn W. Hunton. July 1957. 31p. 
diagrs., tab. (NACA TN 4040. Supersedes 
RM A55D07) 



(1.2. 1.4.3) 
Slotted Flaps 



LOW-SPEED CHORDWISE PRESSURE DISTRIBU- 
TIONS NEAR THE MIDSPAN STATION OF THE 
SLOTTED FLAP AND AILERON OF A 1/4-SCALE 
MODEL OF THE BELL X-l AIRPLANE WITH A 
4-PERCENT -THICK, ASPECT-RATIO-4, UNSWEPT 
WING. William C Moseley, Jr., and Robert T. 
Taylor. March 1954. 59p. diagrs., photos., tabs. 
(NACA RM L53L18) 



THE EFFECTS OF BLOWING OVER VARIOUS 
TRAILING-EDGE FLAPS ON AN NACA 0006 AIR- 
FOIL SECTION, COMPARISONS WITH VARIOUS 
TYPES OF FLAPS ON OTHER AIRFOIL SECTIONS, 
AND AN ANALYSIS OF FLOW AND POWER RELA- 
TIONSHIPS FOR BLOWING SYSTEMS. Jules B. 
Dods, Jr., and Earl C. Watson. June 1956. 145p. 
diagrs., photos., tab. (NACA RM A56C01) 



ESTIMATION OF INCREMENTAL PITCHING MO- 
MENTS DUE TO TRAILING-EDGE FLAPS ON 
SWEPT AND TRIANGULAR WINGS . Harry A . 
James and Lynn W. Hunton. July 1957. 31p. 
diagrs., tab. (NACA TN 4040. Supersedes 
RM A55D07) 



(1.2. 1.4.4) 
Leading-Edge Flaps 



LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS OF AN AIRPLANE MODEL HAVING A 
42 8° SWEPTBACK CIRCULAR- ARC WING WITH 
ASPECT RATIO 4.00, TAPER RATIO 0.50, AND 
SWEPTBACK TAIL SURFACES. Joseph Weil, Paul 
Comisarow, and Kenneth W. Goodson. October 17, 
1947. 84p. diagrs., photos., tab. 
(NACA RM L7G28) 



THE EFFECTS OF BLOWING OVER VARIOUS 
TRAILING-EDGE FLAPS ON AN NACA 0006 AIR- 
FOIL SECTION, COMPARISONS WITH VARIOUS 
TYPES OF FLAPS ON OTHER AIRFOIL SECTIONS, 
AND AN ANALYSIS OF FLOW AND POWER RELA- 
TIONSHD7S FOR BLOWING SYSTEMS, Jules B. 
Dods, Jr., and Earl C. Watson. June 1956. 145p. 
diagrs., photos., tab. (NACA RM A56C01) 



WING LOADS AND LOAD DISTRIBUTIONS THROUGH- 
OUT THE LIFT RANGE OF THE DOUGLAS X-3 
RESEARCH AD3PLANE AT TRANSONIC SPEEDS. 
Earl R. Keener and Gareth H. Jordan. November 
1956. 19 lp. diagrs., photo., tabs. 
(NACA RM H56G13) 



(1.2.1.4.5) 

Slots and Slats 



EFFECTS OF LEADING-EDGE SLATS ON THE 
AERODYNAMIC CHARACTERISTICS OF A 45° 
SWEPTBACK WING-FUSELAGE CONFIGURATION 
AT MACH NUMBERS OF 0.4 TO 1 .03 . Jack F . 

Runckel and Seymour Steinberg. August 1953. 50p. 
diagrs., photos. (NACA RM L53F23) 



HEAT REQUIREMENTS FOR ICE PROTECTION OF 
A CYCLICALLY GAS-HEATED, 36° SWEPT AIR- 
FOIL WITH PARTIAL-SPAN LEADING-EDGE SLAT. 
Vernon H. Gray and Uwe H. von Glahn. May 1956. 
73p. diagrs., photos., tabs. (NACA RM E56B23) 



(1.2.1.5) 
CONTROLS 



A METHOD FOR INCREASING THE EFFECTIVE- 
NESS OF STABILIZING SURFACES AT HIGH SUPER- 
SONIC MACH NUMBERS. Charles H. McLellan. 
August 1954. 14p. diagrs. (NACA RM L54F21) 



(1.2.1.5.1) 
Flap Type 



LOAD DISTRIBUTIONS ASSOCIATED WITH CON- 
TROLS AT SUPERSONIC SPEEDS. K. R. Czarnecki 
and Douglas R. Lord. May 1953. 21p. photo., 
diagrs. (NACA RM L53D15a) 



31 



(1) AERODYNAMICS 



AN INVESTIGATION AT MACH NUMBER 2.40 OF 
FLAP -TYPE CONTROLS EQUIPPED WITH OVER- 
HANG NOSE BALANCES. James N. Mueller. 
November 1953. 95p. diagrs., photos., tab. 
(NACA RM L53I21) 



LOW-SPEED CHGRDWEE PRESSURE DISTRIBU- 
TIONS NEAR THE MIDSPAN STATION OF THE 
SLOTTED FLAP AND AILERON OF A 1/4-SCALE 
MODEL OF THE BELL X-l AIRPLANE WITH A 
4-PERCENT -THICK, ASPECT -RATIO-4, UNSWEPT 
WING. William C . Moseley , Jr ., and Robert T . 
Taylor. March 1954. 59p. diagrs., photos., tabs. 
(NACA RM L53L18) 



(1.2.1.5.2) 

Spoilers 



LOAD DISTRIBUTIONS ASSOCIATED WITH C<$J- 
TROLS AT SUPERSONIC SPEEDS. K. R. Czarneckl 
and Douglas R. Lord. Mav 1953. 21p. photo., 
diagrs.. (NACA RM L53D15a) 



EFFECTS OF RIGID SPOILERS ON THE TWO- 
DIMENSIONAL FLUTTER DERIVATIVES OF AIR- 
FOILS OSCILLATING IN PITCH AT HIGH SUBSONIC 
SPEEDS. James C. Monfort and John A. Wyss., 
December 1954. 33p. diagrs., photos., tabs. 
(NACA RM A54I22) 



AERODYNAMIC LOADINGS ASSOCIATED WITH 
SWEPT AND UNSWEPT SPOILERS ON A FLAT 
PLATE AT MACH NUMBERS OF 1.61 AND 2.01 : 
Douglas R. Lord and K. R. Czarneckl. March 1956. 
174p. diagrs., photos., tabs. (NACA RM L55L12) 



INVESTIGATION OF SPOILERS AT A MACH NUM- 
BER OF 1.93 TO DETERMINE THE EFFECTS OF 
HEIGHT AND CHORDWISE LOCATION ON THE 
SECTION AERODYNAMIC CHARACTERISTICS OF A 
TWO-DIMENSIONAL WING. James N. Mueller. 
February 1958. 52p. diagrs., photos. 
(NACA TN 4180. Supersedes RM L52L31) 



(1.2.1.6) 
BOUNDARY LAYER 



AN INVESTIGATION OF FOUR WINGS OF SQUARE 
PLAN FORM AT A MACH NUMBER OF 6.9 IN THE 
LANGLEY 11 -INCH HYPERSONIC TUNNEL. 
Charles H. McLellan, MitchelH. Bertram, and 
John A. Moore. 1957. ii, 18p. diagrs., photos. 
(NACA Rept. 1310. Supersedes RM L51D17) 



VELOCITY AND FRICTION CHARACTERISTICS OF 
LAMINAR VISCOUS BOUNDARY-LAYER AND 
CHANNEL FLOW OVER SURFACES WITH EJEC- 
TION OR SUCTION. E. R. G. Eckert, Patrick L. 
Donoughe and Betty Jo Moore. December 1957. 
57p. diagrs., tabs. (NACA TN 4102) 



EFFECTS OF LEADING-EDGE BLUNTING ON THE 
LOCAL HEAT TRANSFER AND PRESSURE DISTRI- 
BUTIONS OVER FLAT PLATES IN SUPERSONIC 
FLOW. Marcus O. Creager. December 1957. 
54p. diagrs., tabs. (NACA TN 4142) 



ON FLOW OF ELECTRICALLY CONDUCTING 
FLUIDS OVER A FLAT PLATE IN THE PRESENCE 
OF A TRANSVERSE MAGNETIC FIELD. Vernon J. 
Rossow. 1958. ii, 20p. diagrs., tabs. 
(NACA Rept. 1358. Supersedes TN 3971) 



EFFECTS OF BOUNDARY-LAYER DISPLACEMENT 
AND LEADING-EDGE BLUNTNESS ON PRESSURE 
DISTRIBUTION, SKIN FRICTION, AND HEAT TRANS- 
FER OF BODIES AT HYPERSONIC SPEEDS. 
Mitchel H. Bertram and Arthur Henderson, Jr. 
July 1958. 33p. diagrs. (NACA TN 4301) 



ON POSSIBLE SIMILARITY SOLUTIONS FOR 
THREE-DIMENSIONAL INCOMPRESSIBLE LAMINAR 
BOUNDARY-LAYER FLOW OVER DEVELOPABLE 
SURFACES AND WITH PROPORTIONAL MAIN- 
STREAM VELOCITY COMPONENTS. Arthur G. 
Hansen, Case Institute of Technology. September 
1958. (ii), 79p. diagrs. (NACA TM 1437) 



THE TURBULENT BOUNDARY LAYER ON A ROUGH 
CURVILINEAR SURFACE. (Turbulentnyi 
rogranichnyi sloi na sherpokhovatof krivolineinol 
poverkhnosti.) V. F. Droblenkov. September 1958. 
lOp. diagrs. (NACA TM 1440. Translation from 
Akademila Nauk SSSR, Izvestiia, Otdelenle 
Tekhnichesfcikh Nauk, no. 8, 1955, p, 17-21) 



SIMCLAR SOLUTIONS FOR THE COMPRESSIBLE 
BOUNDARY LAYER ON A YAWED CYLINDER WITH 
TRANSPIRATION COOLING. Ivan E. Beckwith, 
September 1958. 72p. diagrs., tabs. 
(NACA TN 4345) 



SOME NUMERICAL SOLUTIONS OF SIMILARITY 
EQUATIONS FOR THREE-DIMENSIONAL LAMINAR 
INCOMPRESSD3LE BOUNDARY -LAYER FLOWS. 
Peggy L. Yohner and Arthur G. Hansen. September 
1958. 76p. diagrs., tabs. (NACA TN 4370) 



(1.2.1.6.1) 
Characteristics 



A THERMAL SYSTEM FOR CONTINUOUS MONI- 
TORING OF LAMINAR AND TURBULENT ' 
BOUNDARY-LAYER FLOWS DURING ROUTINE 
FLIGHT. Norman R. Richardson and Elmer A. 
Horton. September 1957. 25p. diagrs., photos. 
(NACA TN 4108) 



A LOW-SPEED EXPERIMENTAL INVESTIGATION 
OF THE EFFECT OF A SANDPAPER TYPE OF 
ROUGHNESS ON BOUNDARY -LAYER TRANSITION. 
Albert E. von Doenhoff and Elmer A. Horton. 1958. 
ii, 16p. diagrs., photos. (NACA Rept. 1349. i 
Supersedes TN 3856) 



32 



( 1 ) AERODYNAMICS 



(1.2.1.6.2) 
Control 



THE EFFECTS OF BLOWING OVER VARIOUS 
TRAILING-EDGE FLAPS ON AN NACA 0006 AIR- 
FOIL SECTION, COMPARISONS WITH VARIOUS 
TYPES OF FLAPS ON OTHER AIRFOIL SECTIONS, 
AND AN ANALYSIS OF FLOW AND POWER RELA- 
TIONSHIPS FOR BLOWING SYSTEMS. Jules B. 
Dods, Jr., and Earl C. Watson. June 1956. 145p. 
diagrs., photos., tab. (NACA KM AbbCUl) 



ANALYSIS OF SOME PARAMETERS USED IN 
CORRELATING BLOWING-TYPE BOUNDARY- 
LAYER CONTROL DATA. Mark W. Kelly. 
September 1956. 19p. diagrs. (NACA RM A56F12) 



BOUNDARY-LAYER STABILITY DIAGRAMS FOR 
ELECTRICALLY CONDUCTING FLUIDS IN THE 
PRESENCE OF A MAGNETIC FIELD. Vernon J. 
Rossow. August 1958. 32p. diagrs., tabs. 
(NACA TN 4282) 



(1.2.1.7) 
REYNOLDS NUMBER EFFECTS 



INVESTIGATION OF THE EFFECTS OF PROFDLE 
SHAPE ON THE AERODYNAMIC AND STRUCTURAL 
CHARACTERISTICS OF THIN, TWO-DIMENSIONAL 
AIRFOILS AT SUPERSONIC SPEEDS. Elliott D. 
Katzen, Donald M. Kuehn, and William A. Hill, Jr. 
September 1957. 59p. diagrs., tabs. 
(NACA TN 4039. Supersedes RM A54B08a) 



STUDY OF PRESSURE DISTRIBUTIONS ON SIMPLE 
SHARP -NOSED MODELS AT MACH NUMBERS FROM 
16 TO 18 IN HELIUM FLOW. Wayne D. Erickson. 
October 1957. 42p. diagrs., photos. 
(NACA TN 4113) 



EFFECT OF FLOW INCIDENCE AND REYNOLDS 
NUMBER ON LOW-SPEED AERODYNAMIC CHAR- 
ACTERISTICS OF SEVERAL NONCIRCULAR CYL- 
INDERS WITH APPLICATIONS TO DIRECTIONAL 
STABILITY AND SPINNING. Edward C Polhamus. 
January 1958. 54p. diagrs., photo., tab. 
(NACA TN 4176) 



BOUNDARY-LAYER DISPLACEMENT EFFECTS IN 
AIR AT MACH NUMBERS OF 6.8 AND 9.6. 
Mitchel H. Bertram. February 1958. 61p. diagrs., 
photos. (NACA TN 4133) 



WALL PRESSURE FLUCTUATIONS IN A TURBU- 
LENT BOUNDARY LAYER. William W. Willmarth, 
California Institute of Technology. March 1958. 
39p. diagrs., photo. (NACA TN 4139) 



(1.2. 1.8) 
MACH NUMBER EFFECTS 



DRAG MEASUREMENTS IN FLIGHT ON THE 
10-PERCENT -THICK AND 8 -PERCE NT -THICK 
WING X-l AIRPLANES. John J. Gardner. 
November 19, 1948. 17p. diagrs., photo. 
(NACA RM L8K05) 



TWO-DIMENSIONAL CHORDWISE LOAD DISTRIBU- 
TIONS AT TRANSONIC SPEEDS. Walter F. Lindsey 
and Richards. Dick. February 1952. 41p. diagrs., 
photos. (NACA RM L51I07) 



FLOW AND FORCE CHARACTERISTICS OF 
2-PERCENT -THICK AIRFOILS AT TRANSONIC 
SPEEDS. Walter F. Lindsey and Emma Jean 
Landrum. January 1955. 74p. diagrs., photos. 
(NACA RM L54I30) 



PRELIMINARY FLIGHT-DETERMINED PRESSURE 
DISTRIBUTIONS OVER THE WING OF THE 
DOUGLAS X-3 RESEARCH AIRPLANE AT SUBSONIC 
AND TRANSONIC MACH NUMBERS. Gareth H. 
Jordan and C. Kenneth Hutchins, Jr. April 1955. 
34p. diagrs., photos., tabs. (NACA RM H55A10) 



A STUDY OF LOCAL-PRESSURE FLUCTUATIONS 
RELATIVE TO STATIC -PRESSURE DISTRIBUTIONS 
OF TWO-DIMENSIONAL AIRFOILSAT HIGH SUB- 
SONIC MACH NUMBERS. Charles F. Coe. 
December 1955. 66p. diagrs., photos. 
(NACARM A55J11) 



INVESTIGATION OF UNSTEADY FLOW PAST FOUR 
NACA 6-PERCENT-THICK AIRFOIL SECTIONS. 

Charles L. Ladson and Walter F. Lindsey. July 
1956. 17p. diagrs. (NACA RM L56E14) 



WING LOADS AND LOAD DISTRIBUTIONS THROUGH- 
OUT THE LIFT RANGE OF THE DOUGLAS X-3 
RESEARCH ADXPLANE AT TRANSONIC SPEEDS. 
Earl R. Keener and Gareth H. Jordan. November 
1956. 191p. diagrs., photo., tabs. 
(NACA RM H56G13) 



INVESTIGATION OF THE EFFECTS OF PROFTLE 
SHAPE ON THE AERODYNAMIC AND STRUCTURAL 
CHARACTERISTICS OF THIN, TWO-DIMENSIONAL 
AIRFOILS AT SUPERSONIC SPEEDS. Elliott D. 
Katzen, Donald M. Kuehn, and William A. Hill, Jr. 
September 1957. 59p. diagrs., tabs. 
(NACA TN 4039. Supersedes RM A54B08a) 



STUDY OF PRESSURE DISTRIBUTIONS ON SIMPLE 
SHARP-NOSED MODELS AT MACH NUMBERS FROM 
16 TO 18 IN HELIUM FLOW. Wayne D. Erickson. 
October 1957. 42p. diagrs., photos. 
(NACA TN 4113) 



EFFECT OF ANGLE OF ATTACK AND THICKNESS 
ON AERODYNAMIC COEFFICIENTS OF A RIGID 
WING OSCILLATING AT VERY LOW FREQUENCIES 
IN TWO-DIMENSIONAL SUPERSONIC FLOW. 
Franks. Malvestuto, Jr., and Julia M. Goodwin. 
January 1958. 65p. diagrs. (NACA TN 4069) 



THEORETICAL PRESSURE DISTRIBUTIONS FOR 
SEVERAL RELATED NONLIFTING AIRFOILS AT 
HIGH SUBSONIC SPEEDS. John R. Spreiter, 
Alberta Y. Alksne, andB. Jeanne Hyett. January 
1958. (i), 52p. diagrs., tab. (NACA TN 4148) 



BOUNDARY-LAYER DISPLACEMENT EFFECTS IN 
AIR AT MACH NUMBERS OF 6.8 AND 9.6. 
Mitchel H. Bertram. February 1958. 61p. diagrs., 
photos. (NACA TN 4133) 



33 



(1) AERODYNAMICS 



COMPILATION OF INFORMATION ON THE TRAN- 
SONIC ATTACHMENT OF FLOWS AT THE LEAD- 
ING EDGES OF AIRFOILS. Walter F. Lindsey and 
Emma Jean Landrum. February 1958. 63p. 
diagrs., photos., tabs. (NACA TN 4204) 



(1.2.1-9) 
WAKE 



AN INVESTIGATION AT MACH NUMBERS OF 1-62 
AND 1.93 OF THE LIFT EFFECTIVENESS AND 
INTEGRATED DOWNWASH CHARACTERISTICS OF 
SEVERAL IN-LINE MISSILE CONFIGURATIONS 
HAVING EQUAL-SPAN WINGS AND TAILS. Carl E. 
Grigsby. April 1952. 75d. diagrs., tabs. 
(NACA RM L52A02) 



AERODYNAMIC EFFECTS CAUSED BY ICING OF 
AN UNSWEPT NACA 65A004 AIRFOIL. Vernon H. 
Gray and Uwe H. von Glahn. February 1958. 47p. 
diagrs., photos., tabs. (NACA TN 4155) 



(1A2) 



INVESTIGATION OF INTERFERENCE LIFT, DRAG, 
AND PITCHING MOMENT OF A SERIES OF REC- 
TANGULAR WING AND BODY COMBINATIONS AT 
MACH NUMBERS OF 1.62, 1.93, AND 2.41. Donald 
E. Coletti. August 1952. 74p. diagrs., tabs. 
(NACA RM L52E26) 



LIFT, DRAG, AND PITCHING MOMENT OF LOW- 
ASPECT-RATIO WINGS AT SUBSONIC AND SUPER- 
SONIC SPEEDS. Charles F. Hall. April 1953. 
132p. diagrs., tabs. (NACA RM A53A30) 



A WIND-TUNNEL INVESTIGATION OF THE USE 
OF SPOILERS FOR OBTAINING STATIC LONGITU- 
DINAL STABILITY OF A CANARD -MISSILE MODEL 
IN REVERSE FLIGHT. Herman S. Fletcher. June 
1954. 15p. diagrs., tab. (NACA RM L54E05) 



WING PRESSURE DISTRIBUTIONS OVER THE LIFT 
RANGE OF THE CONVAIR XF-92A DELTA-WING 
AIRPLANE AT SUBSONIC AND TRANSONIC 
SPEEDS. Earl R. Keener and Gareth H. Jordan. 
November 1955. 135p. diagrs., photos., tabs. 
(NACA RM H55G07) 



AN INVESTIGATION OF FOUR WINGS OF SQUARE 
PLAN FORM AT A MACH NUMBER OF 6.9 IN THE 
LANGLEY U-INCH HYPERSONIC TUNNEL. 
Charles H. McLellan, MitchelH. Bertram, and 
John A. Moore. 1957. ii, 18p. diagrs., photos. 
(NACA Rept. 1310. Supersedes RM L51D17) 



EFFECT OF FREQUENCY OF SIDESLIPPING 
MOTION ON THE LATERAL STABILITY DERIVA- 
TIVES OF A TYPICAL DELTA-WING AIRPLANE. 
Jacob H. Llchtenstein and James L. Williams. 
September 1957. 46p. diagrs., photos., tabs. 
(NACA RM L57F07) 



ELLIPTIC CONES ALONE AND WITH WINGS AT 
SUPERSONIC SPEEDS. Lcland H. Jorgensen. 
October 1957. 55p. diagrs., photos. 
(NACA TN 4045) 



(1.2.2. 1) 
WING THEORY 



WING LOAD DISTRIBUTION ON A SWEPT-WING 
AIRPLANE IN FLIGHT AT MACH NUMBERS UP TO 
1.11 AND COMPARISON WITH THEORY. L. Stewart 
Rolls and Frederick H. Matteson. April 1952. 73p. 
diagrs., photos., tabs. (NACA RM A52A31) 



HINGE -MOMENT CHARACTERISTICS FOR SEVER- 
AL TIP CONTROLS ON A 60° SWEPTBACK DELTA 
WING AT MACH NUMBER 1.61. K. R. Czarnecki 
and Douglas R. Lord. January 1953. 31p. diagrs., 
photos. (NACA RM L52K28) 



LOAD DISTRIBUTIONS ASSOCIATED WITH CON- 
TROLS AT SUPERSONIC SPEEDS. K. R. Czarnecki 
and Douglas R. Lord. May 1953. 21p. photo., 
diacrs. (NACA RM L 5 3D 15a) 



EFFECT OF SOME SECTION MODIFICATIONS AND 
PROTUBERANCES ON THE ZERO-LIFT DRAG OF 
DELTA WINGS AT TRANSONIC AND SUPERSONIC 
SPEEDS. Carl A. Sandahl and William E. Stoney. 
February 1954. 43p. diagrs., photos., tabs. 
(NACA RM L53L24a) 



AERODYNAMIC CHARACTERISTICS OF A FULL- 
SPAN TRAILING-EDGE CONTROL ON A 60° DELTA 
WING WITH AND WITHOUT A SPOILER AT MACH 
NUMBER 1.61. Douglas R. Lord and K. R. 
Czarnecki. March 1954. 49p. diagrs., photos., 
tab. (NACA RM L53L17) 



AERODYNAMIC CHARACTERISTICS OF SEVERAL 
TIP CONTROLS ON A 60° DELTA WING AT A MACH 
NUMBER OF 1.61. Douglas R. Lord and K. R. 
Czarnecki. August 1954. 44p. diagrs., photos., 
tabs. (NACA RM L54E25) 



EFFECTS OF OVERHANG BALANCE ON THE 
HINGE-MOMENT AND EFFECTIVENESS CHARAC- 
TERISTICS OF AN UNSWEPT TRAILING-EDGE 
CONTROL ON A 60° DELTA WING AT TRANSONIC 
AND SUPERSONIC SPEEDS. Lawrence D. Guy. 
September 1954. 48p. diagrs., photo. 
(NACA RM L54G12a) 



THE ROLLING MOMENT DUE TO SIDESLIP OF 
SWEPT WINGS AT SUBSONIC AND TRANSONIC 
SPEEDS. Edward C Polhamus and William C ■ 
Sleeman, Jr. March 1955. 81p. diagrs., photos., 
tabs. (NACA RM L54L01) 



TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF SWEEPBACK AND THICKNESS 
RATIO ON THE WING LOADS OF A WING-BODY 
COMBINATION OF ASPECT RATIO 4 AND TAPER 
RATIO 0.6. Robert J. Piatt, Jr., and Joseph D. 
Brooks. April 1955. 44p. diagrs., photos., tab. 
(NACA RM L54L31b) 



34 



(1) AERODYNAMICS 



INVESTIGATION OF THE EFFECTS OF AN AIRFOIL 
SECTION MODIFICATION ON THE AERODYNAMIC 
CHARACTERISTICS AT SUBSONIC AND SUPERSONIC 
SPEEDS OF A THIN SWEPT WING OF ASPECT 
RATIO 3 IN COMBINATION WITH A BODY . David 
Graham and William T. Evans. Jane 1955. 46p. 
diagrs., tabs. (NACA RM A55D11) 



A STUDY OF CONICAL CAMBER FOR TRIANGULAR 
AND SWEPTBACK WINGS. John W. Boyd, Eugene 
Migotsky, and Benton E. Wetzel. November 1955. 
79p. diagrs., tabs. (NACA RM A55G19) 



TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE AERODYNAMIC LOADING CHARACTERISTICS 
OF A HIGHLY TAPERED UNSWEPT WING IN THE 
PRESENCE OF A BODY WITH AND WITHOUT IN- 
DENTATION. Joseph D. Brooks. February 1956. 
30p. diagrs., photos., tab. (NACA RM L55J20) 



EFFECT OF WING CAMBER AND TWIST AT MACH 
NUMBERS FROM 1.4 TO 2.1 ON THE LIFT, DRAG, 
AND LONGITUDINAL STABILITY OF A ROCKET- 
POWERED MODEL HAVING A 52.5° SWEPTBACK 
WING OF ASPECT RATIO 3 AND INLINE TAIL SUR- 
FACES. Warren Gillespie, Jr. May 1956. 29p. 
diagrs., photos., tabs. (NACA RM L56C16) 



A THEORETICAL STUDY OF THE AERODYNAMICS 
OF SLENDER CRUCIFORM-WING ARRANGEMENTS 
AND THEIR WAKES. John R. Spreiter and Alvin H- 
Sacks. 1957. ii, 31p. diagrs., photos., tabs. 
(NACA Rept. 1296. Supersedes TN 3528) 



THREE-DIMENSIONAL TRANSONIC FLOW THEORY 
APPLIED TO SLENDER WINGS AND BODIES. 
Max. A. Heaslet and John R. Spreiter. 1957. 
Hi, 29p. diagrs. (NACA Rept. 1318. Supersedes 
TN 3717) 



THEORETICAL CALCULATION OF THE POWER 
SPECTRA OF THE ROLLING AND YAWING 
MOMENTS ON A WING IN RANDOM TURBULENCE. 
John M. Eggleston and Franklin W. Diederich. 
1957. ii, 19p. diagrs., tabs. (NACA Rept. 1321. 
Supersedes TN 3864.) 



METHOD FOR CALCULATING THE AERODYNAMIC 
LOADING ON AN OSCILLATING FINITE WING IN 
SUBSONIC AND SONIC FLOW. Harry L. Runyan 
and Donald S. Woolston. 1957. ii, 30p. diagrs., 
tabs. (NACA Rept. 1322. Supersedes TN 3694) 



THEORETICAL AND EXPERIMENTAL INVESTIGA- 
TION OF THE SUBSONIC-FLOW FIELDS BENEATH 
SWEPT AND UNSWEPT WINGS WITH TABLES OF 
VORTEX-INDUCED VELOCITIES. William J. 
Alford, Jr. 1957. ii, 43p. diagrs., photo., tabs. 
(NACA Rept. 1327. Supersedes TN 3738) 



THE MINIMIZATION OF WAVE DRAG FOR WINGS 
AND BODIES WITH GIVEN BASE AREA OR 
VOLUME. Max. A. Heaslet. July 1957. 27p. 
(NACA TN 3289) 



THE USE OF PURE TWIST FOR DRAG REDUCTION 
ON ARROW WINGS WITH SUBSONIC LEADING 
EDGES. Frederick C Grant. August 1957. 28p. 
diagrs., tabs. (NACA TN 4104) 



EXPERIMENTAL INVESTIGATION OF LIFT, DRAG, 
AND PITCHING MOMENT OF FIVE ANNULAR AIR- 
FOILS. Hermans. Fletcher. October 1957. 
25p. diagrs., photos. (NACA TN 4117) 



LIFT AND MOMENT ON THIN ARROWHEAD WINGS 
WITH SUPERSONIC EDGES OSCILLATING IN 
SYMMETRIC FLAPPING AND ROLL AND APPLI- 
CATION TO THE FLUTTER OF AN ALL-MOVABLE 
CONTROL SURFACE. H. J. Cunningham. January 
1958. 58p. diagrs. (NACA TN 4189) 



DRAG MINIMIZATION FOR WINGS IN SUPERSONIC 
FLOW, WITH VARIOUS CONSTRAINTS. Max. A. 
Heaslet and Franklyn B. Fuller. February 1958. 
30p. (NACA TN 4227) 



EXPERIMENTAL STUDY OF THE EQUIVALENCE 
OF TRANSONIC FLOW ABOUT SLENDER CONE- 
CYLINDERS OF CIRCULAR AND ELLIPTIC CROSS 
SECTION. William A. Page. April 1958. 45p. 
diagrs., photos., tab. (NACA TN 4233) 



GENERAL SOLUTIONS FOR FLOW PAST SLENDER 
CAMBERED WINGS WITH SWEPT TRAILING EDGES 
AND CALCULATION OF ADDITIONAL LOADING 
DUE TO CONTROL SURFACES. E. B. Klunker 
and Keith C. Harder. May 1958. 55p. diagrs. 
(NACA TN 4242) 



IDEALIZED WINGS AND WTNG-BODIES AT A MACH 
NUMBER OF 3. Elliott D. Katzen. July 1958. lip. 
diagrs. (NACA TN 4361) 



(1.2.2.2) 
WING VARIABLES 



REVIEW OF THE MAXIMUM-LIFT CHARACTER- 
ISTICS OF THIN AND SWEPT WINGS. Joh^G. 
Lowry and Jones F. Cahill. June 5, 1951. lOp. 
diagrs. (NACA RM L51E03) 



LIFT, DRAG, AND PITCHING MOMENT OF LOW- 
ASPECT-RATIO WINGS AT SUBSONIC AND SUPER- 
SONIC SPEEDS - TWISTED AND CAMBERED TRI- 
ANGULAR WING OF ASPECT RATIO 2 WITH NACA 
0003-63 THICKNESS DISTRIBUTION. Charles F. 
Hall and John C. Heitmeyer. June 12, 1951. 24p. 
diagrs., photo., tab. (NACA RM A51E01) 



LIFT, DRAG, AND PITCHING MOMENT OF LOW- 
ASPECT-RATIO WINGS AT SUBSONIC AND SUPER- 
SONIC SPEEDS - TWISTED AND CAMBERED TRI- 
ANGULAR WING OF ASPECT RATIO 2 WITH NACA 
0005-63 THICKNESS DISTRIBUTION. John C. 
Heitmeyer and Robert B. Petersen. April 1952. 
20p. diagrs., tabs. (NACA RM A52B08) 



AERODYNAMIC CHARACTERISTICS EXTENDED TO 
HIGH ANGLES OF ATTACK AT TRANSONIC SPEEDS 
OF A SMALL-SCALE 0° SWEEP WING, 45° SWEPT- 
BACK WING, AND 60° DELTA WTNG. Harleth G. 
Wiley. November 1952. 26p. diagrs. 
(NACA RM L52I30) 



35 



(1) AERODYNAMICS 



LIFT, DRAG, AND PITCHING MOMENT OF LOW- 
ASPECT-RATIO WINGS AT SUBSONIC AND SUPER- 
SONIC SPEEDS. Charles F. Hall. April 1953. 
132p. diagrs., tabs. (NACA RM A53A30) 



LOAD DISTRIBUTIONS ASSOCIATED WITH CON- 
TROLS AT SUPERSONIC SPEEDS- K. R. Czarnecki 
and Douglas R. Lord. Mav 1953. 21p. photo. 
diagrs. (NACA RM L53D15a) 



EFFECTS OF A SERIES OF INBOARD PLAN -FORM 
MODIFICATIONS ON THE LONGITUDINAL CHAR- 
ACTERISTICS OF TWO 47° SWEPTBACK WINGS OF 
ASPECT RATIO 3.5, TAPER RATIO 0.2, AND DIF- 
FERENT THICKNESS DISTRIBUTIONS AT MACH 
NUMBERS OF 1.61 AND 2.01. Morton Cooper and 
JohnR. Sevier, Jr. July 1953. 43p. diagrs., 
photos., tabs. (NACA RM L53E07a) 



THE INFLUENCE OF A CHANGE IN BODY SHAPE 
ON THE EFFECTS OF TWIST AND CAMBER AS 
DETERMINED BY A TRANSONIC WIND-TUNNEL 
INVESTIGATION OF A 45° SWEPTBACK WING- 
FUSELAGE CONFIGURATION. Daniel E. Harrison. 
August 1953. 23p. diagrs., tab. 
(NACA RM L53B03) 



EFFECTS OF A SERIES OF INBOARD PLAN-FORM 
MODIFICATIONS ON THE LONGITUDINAL CHAR- 
ACTERISTICS OF TWO UNSWEPT WINGS OF AS- 
PECT RATIO 3.5, TAPER RATIO 0.2, AND DIF- 
FERENT THICKNESS DISTRIBUTIONS AT MACH 
NUMBERS OF 1.61 AND 2.01. John R. Sevier, Jr. 
February 1954. 43p. diagrs., photos. 
(NACA RM L53K11) 



AERODYNAMIC CHARACTERISTICS OF SEVERAL 
TIP CONTROLS ON A 60° DELTA WING AT A MACH 
NUMBER OF 1.61. Douglas R. Lord and K. R. 
Czarnecki. August 1954. 44p. diagrs., photos., 
tabs. (NACA RM L54E25) 



WING PRESSURE DISTRIBUTIONS AT LOW LIFT 
FOR THE XF-92A DELTA-WING AIRPLANE AT 
TRANSONIC SPEEDS. Earl R. Keener. October 

1954. 54p. diagrs., photos., tabs. 
(NACA RM H54H06) 



A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE LONGITUDINAL FORCE AND MOMENT CHAR- 
ACTERISTICS OF TWO DELTA WINGS AND ONE 
CLIPPED-TIP DELTA WING OF 4 PERCENT 
THICKNESS ON A SLENDER BODY . William E . 
Palmer and Dale L. Burrows. April 1955. 31p. 
diagrs., photo. (NACA RM L55A07a) 



A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE STATIC LONGITUDINAL CHARACTERISTICS 
OF A 3-PERCENT -THICK, ASPECT-RATIO-3, 
DELTA WING CAMBERED AND TWISTED FOR HIGH 
LIFT-DRAG RATIOS. Dale L. Burrows and Warren 
A. Tucker. August 1955. 38p. diagrs., photos., 
tab. (NACA RM L55F02a) 



A STUDY OF CONICAL CAMBER FOR TRIANGULAR 
AND SWEPTBACK WINGS. John W. Boyd, Eugene^ 
Migotsky, and Benton E. Wetzel. November 1955 
79p. diagrs., tabs. (NACA RM A55G19) 



EFFECT OF AIRPLANE CONFIGURATION ON 
STATIC STABDLITY AT SUBSONIC AND TRANSONIC 
SPEEDS. Edward C. Polhamus and Joseph M. 
Hallissy, Jr. May 1956. 17p- diagrs. 
(NACA RM L56A09a) 



EFFECT OF WING CAMBER AND TWIST AT MACH 
NUMBERS FROM 1.4 TO 2.1 ON THE LIFT, DRAG, 
AND LONGITUDINAL STABILITY OF A ROCKET- 
POWERED MODEL HAVING A 52. 5» SWEPTBACK 
WING OF ASPECT RATIO 3 AND INLINE TAIL SUR- 
FACES. Warren GiUespie, Jr. May 1956. 29p. 
diagrs., photos., tabs. (NACA RM L56C16) 



TRANSONIC WIND-TUNNEL INVESTIGATION OF 
STATIC LONGITUDINAL FORCE AND MOMENT 
CHARACTERISTICS OF TWO WING-BODY COMBI- 
NATIONS WITH CLD7PED-TD? AND FULL DELTA 
WINGS OF ASPECT RATIO 1.73. Dale L. Burrows. 
September 1956. 26p. diagrs. (NACA RM L56F21) 



THEORETICAL CALCULATION OF THE POWER 
SPECTRA OF THE ROLLING AND YAWING 
MOMENTS ON A WING IN RANDOM TURBULENCE. 
John M. Eggleston and Franklin W. Diederich. 
1957. ii, 19p. diagrs., tabs. (NACA Rept. 1321. 
Supersedes TN 3864. ) 



A SUMMARY AND ANALYSIS OF THE LOW -SPEED 
LONGITUDINAL CHARACTERISTICS OF SWEPT 
WINGS AT HIGH REYNOLDS NUMBER. G. Chester 
Furlong and James G. McHugh. 1957. ill, 149p. 
diagrs., tabs. (NACA Rept. 1339. Supersedes 
RM L52D16) 



THE USE OF PURE TWIST FOR DRAG REDUCTION 
ON ARROW WINGS WITH SUBSONIC LEADING 
EDGES. Frederick C. Grant. August 1957. 28p. 
diagrs., tabs. (NACA TN 4104) 



THEORETICAL CALCULATIONS OF SUPERSONIC 
WAVE DRAG AT ZERO LIFT FOR A PARTICULAR 
STORE ARRANGEMENT. Kenneth Margolis, 
Frank S. Malvestuto, Jr., and Peter J. Marie, Jr. 
January 1958. 37p. diagrs., tab. (NACA TN 4120) 



INVESTIGATION OF MINIMUM DRAG AND MAXI- 
MUM LIFT-DRAG RATIOS OF SEVERAL WTNG-BODY 
COMBINATIONS INCLUDING A CAMBERED TRI- 
ANGULAR WING AT LOW REYNOLDS NUMBERS 
AND AT SUPERSONIC SPEEDS. Clinton E. Brown 
and L. K. Har grave. September 1958. 62p. diagrs., 
photos., tabs. (NACA TN 4020. Supersedes 
RM L51E11) 



(1.2.2.2.1) 
Profiles 



REVIEW OF THE MAXIMUM-LIFT CHARACTER- 
ISTICS OF THTN AND SWEPT WINGS. JohwG. 
Lowry and Jones F. Cahill. June 5, 1951. lOp. 
diagrs. (NACA RM L51E03) 



36 



(1) AERODYNAMICS 



FREE -FLIGHT MEASUREMENTS AT MACH NUM- 
BERS FROM 0.7 TO 1.6 OF SOME EFFECTS OF 
AIRFOIL-THICKNESS DISTRIBUTION AND 
TRAILING-EDGE ANGLE ON AILERON ROLLING 
EFFECTIVENESS AND DRAG FOR WINGS WITH 0° 
AND 45° SWEEPBACK. E. M. Fields and H. Kurt 
Strass. October 1951. 63p. diagrs., photos., tab. 
(NACA RM L51G27) 



AN INVESTIGATION AT TRANSONIC SPEEDS OF 
THE EFFECTS OF THICKNESS RATIO AND OF 
THICKENED ROOT SECTIONS ON THE AERODY- 
NAMIC CHARACTERISTICS OF WINGS WITH 47° 

RATIO 0.2 IN THE SLOTTED TEST SECTION OF 
THE LANGLEY 8-FOOT HIGH-SPEED TUNNEL. 
Ralph P. Bielat, Daniel E. Harrison, and Domenic A. 
Coppolino. October 1951. 38p. diagrs., photo., tab. 
(NACA RM L5 1104a) 



AERODYNAMIC CHARACTERISTICS AT SUPER- 
SONIC SPEEDS OF A SERIES OF WING-BODY 
COMBINATIONS HAVING CAMBERED WINGS WITH 
AN ASPECT RATIO OF 3.5 AND A TAPER RATIO OF 
0.2. EFFECTS OF SWEEP ANGLE AND THICKNESS 
RATIO ON THE STATIC LATERAL STABILITY 
CHARACTERISTICS AT M = 1.60. M. Leroy 
Spearman and John H. Hilton, Jr. January 1952. 
31p. diagrs., tabs. (NACA RM L51K15a) 



AERODYNAMIC CHARACTERISTICS AT SUPER- 
SONIC SPEEDS OF A SERIES OF WING-BODY 
COMBINATIONS HAVING CAMBERED WINGS WITH 
AN ASPECT RATIO OF 3.5 AND A TAPER RATIO 
OF 0.2. EFFECTS OF SWEEP ANGLE AND THICK- 
NESS RATIO ON THE AERODYNAMIC CHARACTER- 
ISTICS IN PITCH AT M = 1.60. Ross B. Robinson 
and Cornelius Driver. January 1952. 27p. diagrs., 
photos., tabs. (NACA RM L51K16a) 



AN INVESTIGATION AT MACH NUMBERS OF 1.62 
AND 1.93 OF THE LIFT EFFECTIVENESS AND 
INTEGRATED DOWNWASH CHARACTERISTICS OF 
SEVERAL IN-LINE MISSILE CONFIGURATIONS 
HAVING EQUAL-SPAN WINGS AND TAILS. Carl E . 
Grigsby. April 1952. 75p. diagrs., tabs. 
(NACA RM L52A02) 



AERODYNAMIC CHARACTERISTICS AT SUPER- 
SONIC SPEEDS OF A SERIES OF WING-BCDY COM- 
BINATIONS HAVING CAMBERED WINGS WITH AN 
ASPECT RATIO OF 3.5 AND A TAPER RATIO OF 
0.2. EFFECTS OF SWEEP ANGLE AND THICKNESS 
RATIO ON THE AERODYNAMIC CHARACTERISTICS 
IN PITCH AT M = 2.01. Ross B. Robinson. July 
1952. 27p. diagrs., photo., tabs. 
(NACA RM L52E09) 



AERODYNAMIC CHARACTERISTICS AT SUPER- 
SONIC SPEEDS OF A SERIES OF WING-BODY COM- 
BINATIONS HAVING CAMBERED WINGS WITH AN 
ASPECT RATIO OF 3,5 AND A TAPER RATIO OF 
0.2. EFFECTS OF SWEEP ANGLE AND THICKNESS 
RATIO ON THE STATIC LATERAL STABILITY 
CHARACTERISTICS AT M = 2.01. Clyde V. 
Hamilton. August 1952. 37p. diagrs., tabs. 
(NACA RM L52E23) 



AERODYNAMIC CHARACTERISTICS EXTENDED TO 
HIGH ANGLES OF ATTACK AT TRANSONIC SPEEDS 
OF A SMALL-SCALE 0° SWEEP WING, 450 SWEPT - 
BACK WING , AND 60° DE LTA WING . Harleth G . 
Wiley. November 1952. 26p. diagrs. 
(NACA RM L52I30) 



LIFT, DRAG, AND PITCHING MOMENT OF LOW- 
ASPECT-RATIO WINGS AT SUBSONIC AND SUPER- 
SONIC SPEEDS. Charles F. Hall. April 1953. 
132p. diagrs., tabs. (NACA RM A53A30) 



LONGITUDINAL CHARACTERISTICS OF WINGS. 
Thomas A. Toll. October 1953. 18p. diagrs. 
(NACA RM L53I21b) 



DRAG DUE TO LIFT AT MACH NUMBERS UP TO 2.0. 
Edward C. Polhamus. November 1953 . 18p. diagrs. 



EFFECT OF SOME SECTION MODIFICATIONS AND 
PROTUBERANCES ON THE ZERO-LIFT DRAG OF 
DELTA WINGS AT TRANSONIC AND SUPERSONIC 
SPEEDS. Carl A. Sandahl and William E. Stoney. 
February 1954. 43p. diagrs., photos., tabs. 
(NACA RM L53L24a) 



EFFECT OF NOSE SHAPE AND TRAILING-EDGE 
BLUNTNESS ON THE AERODYNAMIC CHARACTER- 
ISTICS OF AN UNSWEPT WING OF ASPECT RATIO 
3.1, TAPER RATIO 0.4, AND 3-PERCENT THICK- 
NESS. John C. Heitmeyer. March 1954. 36p. 
diagrs., tabs. (NACA RM A54A04) 



THE EFFECT OF CANOPY LOCATION ON THE 
AERODYNAMIC CHARACTERISTICS OF A SWEPT- 
BACK WING-BODY CONFIGURATION AT TRAN- 
SONIC SPEEDS. Harold L. Robinson. June 1954. 
14p. diagrs., photo. (NACA RM L54E11) 



A METHOD FOR INCREASING THE EFFECTIVE- 
NESS OF STABILIZING SURFACES AT HIGH SUPER- 
SONIC MACH NUMBERS. Charles H. McLellan 
August 1954. 14p. diagrs. (NACA RM L54F21) 



LONGITUDINAL STABILITY CHARACTERISTICS IN 
ACCELERATED MANEUVERS AT SUBSONIC AND 
TRANSONIC SPEEDS OF THE DOUGLAS D-558-II 
RESEARCH AIRPLANE EQUIPPED WITH A 
LEADING-EDGE WING CHORD-EXTENSION. Jack 
Fischel and Cyril D. Brunn. October 1954. 62p. 
diagrs., photos., tab. (NACA RM H54H16) 



EFFECTS OF INCREASING REYNOLDS NUMBER 
FROM 2 x 106 TO 6 x 106 ON THE AERODYNAMIC 
CHARACTERISTICS AT TRANSONIC SPEEDS OF A 
450 SWEPT WING WITH G° LEADING-EDGE DROOP. 
James W. Schmeer and J . Lawrence Cooper. 
February 1955. 22p. diagrs., photo. 
(NACA RM L54L10) 



TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF SWEEPBACK AND THICKNESS 
RATIO ON THE WING LOADS OF A WING-BODY 
COMBINATION OF ASPECT RATIO 4 AND TAPER 
RATIO 0.6. Robert J. Piatt, Jr., and Joseph D. 
Brooks. April 1955. 44p. diagrs., photos., tab- 
(NACA RM L54L31b) 



INVESTIGATION OF THE EFFECTS OF AN AIRFOIL 
SECTION MODIFICATION ON THE AERODYNAMIC 
CHARACTERISTICS AT SUBSONIC AND SUPERSONIC 
SPEEDS OF A THIN SWEPT WING OF ASPECT 
RATIO 3 IN COMBINATION WITH A BODY. David 
Graham and William T. Evans. June 1955. 46p. 
diagrs., tabs. (NACA RM A55D11) 



37 



( 1 ) AERODYNAMICS 



COLLECTION AND SUMMARY OF FLAP -TYPE- 
AILERON ROLLING-EFFECTIVENESS DATA AT 
ZERO LIFT AS DETERMINED BY ROCKET - 
POWERED MODEL TESTS AT MACH NUMBERS 
BETWEEN 0.6 AND 1.6. H. Kurt Strass, Emily W. 
Stephens, E. M. Fields, and Eugene D. Schult. 
September 1955. 95p. diagrs., photos., tabs. 
(NACA RM L55F14) 



EFFECTS OF LEADING-EDGE RADIUS ON THE 
LONGITUDINAL STABILITY OF TWO 45° SWEPT - 
BACK WINGS INCORPORATING LEADING-EDGE 
CAMBER AS INFLUENCED BY REYNOLDS NUM- 
BERS UP TO 8.00 x 10 6 AND MACH NUMBERS UP 
TO 0.290. Gerald V. Foster. October 1955. 44p. 
diagrs. (NACA RM L55H04) 



A STUDY OF CONICAL CAMBER FOR TRIANGULAR 
AND SWEPTBACK WINGS. JohnW. Boyd, Eugene 
Mi got sky, and Benton E. Wetzel. November 1955. 
79p. diagrs., tabs. (NACA RM A55G19) 



SOME EFFECTS OF SWEEP AND THICKNESS ON 
THE EXPERIMENTAL DOWNWASH CHARACTER- 
ISTICS AT TRANSONIC SPEEDS OF A SERIES OF 
HIGHLY TAPERED WINGS WITH AN ASPECT RATIO 
OF 3. TRANSONIC -BUMP METHOD. Albert G. 
Few, Jr. February 1956. 65p. diagrs., photo. 
(NACARM L55J12) 



EFFECTS OF LEADING-EDGE RADIUS ON THE 
LONGITUDINAL STABILITY CHARACTERISTICS OF 
TWO 60° SWEPTBACK WINGS AT HIGH REYNOLDS 
NUMBERS. William C. Schneider. March 1956. 
46p. diagrs. (NACA RM L55L30) 



EFFECTS OF REYNOLDS NUMBER AND LEADING- 
EDGE SHAPE ON THE LOW-SPEED LONGITUDINAL 
STABILITY OF A 6-PERCENT-THICK 45° SWEPT- 
BACK WING. William C. Schneider. April 1956. 
32p. diagrs. (NACA RM L56B14) 



DATA FROM LARGE-SCALE LOW -SPEED TESTS 
OF AIRPLANE CONFIGURATIONS WITH A THIN 45° 
SWEPT WING INCORPORATING SEVERAL 
LEADING-EDGE CONTOUR MODIFICATIONS. 

William T. Evans. May 1956. HOp. diagrs., 
photo., tabs. {NACA RM A56B17) 



EFFECT OF SEVERAL WING MODIFICATIONS ON 

THE SUBSONIC AND TRANSONIC LONGITUDINAL 
HANDLING QUALITIES OF THE DOUGLAS D-558-II 
RESEARCH AIRPLANE. Jack Fischel and Donald 
Reisert. June 1956. 57p. diagrs., photos., tabs. 
(NACA RM H56C30) 



THE EFFECT OF CONICAL CAMBER ON THE 
STATIC LONGITUDINAL, LATERAL, AND DIREC- 
TIONAL CHARACTERISTICS OF A 45° SWEPTBACK 
WING AT MACH NUMBERS UP TO 0.96. Robert I. 
Sammonds and Robert M. Reynolds. July 1956. 
64p. diagrs., tabs. (NACA RM A56D02) 



WIND-TUNNEL INVESTIGATION OF THE EFFECTS 
OF WING THICKNESS ON THE STATIC LONGITU- 
DINAL AND LATERAL STABILITY OF UNSWEPT 
WINGS OF ASPECT RATIO 3 AT HIGH SUBSONIC 
SPEEDS. William C. Hayes, Jr., and Edward C. 
Polhamus. August 1956. 43p. diagrs., photos. 
(NACA RM L56E30a) 



AN INVESTIGATION OF FOUR WINGS OF SQUARE 
PLAN FORM AT A MACH NUMBER OF 6.9 IN THE 
LANG LEY 11 -INCH HYPERSONIC TUNNEL. 
Charles H. McLellan, MitchelH. Bertram, and 
John A. Moore. 1957. ii, 18p. diagrs., photos. 
(NACARept. 1310. Supersedes RM L51D17) 



EFFECT OF FREQUENCY OF SIDESLIPPING 
MOTION ON THE LATERAL STABILITY DERIVA- 
TIVES OF A TYPICAL DELTA-WING AIRPLANE. 
Jacob H. Lichtenstein and James L. Williams. 
September 1957. 46p. diagrs., photos., tabs. 
(NACA RM L57F07) 



A METHOD FOR THE CALCULATION OF WAVE 
DRAG ON SUPERSONIC-EDGED WINGS AND BI- 
PLANES. Harvard Lomax and Loma Sluder. 
March 1958. 24p. (NACA TN 4232) 



LOW -SPEED EXPERIMENTAL DETERMINATION OF 
THE EFFECTS OF LEADING-EDGE RADIUS AND 
PROFILE THICKNESS ON STATIC AND OSCILLA- 
TORY LATERAL STABILITY DERIVATIVES FOR A 
DELTA WING WITH 60° OF LEADING-EDGE SWEEP. 
Hermans. Fletcher. July 1958. 4 5p. diagrs., 
photos., tabs. (NACA TN 4341) 



IDEALIZED WINGS AND WING- BODIES AT A MACH 
NUMBER OF 3. Elliott D. Katzen. July 1958. lip. 
diagrs. (NACA TN 4361) 



THE STATIC LONGITUDINAL CHARACTERISTICS 
OF A TWISTED AND CAMBERED 45° SWEPTBACK 
WING AT MACH NUMBERS UP TO 0.96. Robert I. 
Sammonds and Robert M. Reynolds. August 1958. 
26p. diagrs., tab. (NACA RM A58C21) 



(1.2.2.2.2) 
Aspect Ratio 



PRELIMINARY INVESTIGATION OF THE LOW- 
AMPLITUDE DAMPING IN PITCH OF TAILLESS 
DELTA- AND SWEPT-WING CONFIGURATIONS AT 
MACH NUMBERS FROM 0.7 TO 1.35. Charles T. 
D»Aiutolo and Robert N. Parker. August 1952. 27p. 
diagrs., photos., tab. (NACA RM L52G09) 



TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF ASPECT RATIO, SPANWISE 
VARIATIONS IN SECTION THICKNESS RATIO, AND 
A BODY INDENTATION ON THE AERODYNAMIC 
CHARACTERISTICS OF A 45° SWEPTBACK WING- 
BODY COMBINATION. Melvin M. Carmel. 
January 1953. 44p. diagrs., tab. 
(NACA RM L52L26b) 



LIFT, DRAG, AND PITCHING MOMENT OF LOW- 
ASPECT-RATIO WINGS AT SUBSONIC AND SUPER- 
SONIC SPEEDS. Charles F. Hall. April 1953. 
132p. diagrs., tabs. (NACA RM A53A30) 



38 



(1) AERODYNAMICS 



INVESTIGATION OF WING FLUTTER AT TRAN- 
SONIC SPEEDS FOR SIX SYSTEMATICALLY VARIED 
WING PLAN FORMS. George W. Jones, Jr., and 
Hugh C. DuBose. August 1953. 32p. diagrs., ' 
photos., 3 tabs. (NACA RM L53G10a) 



A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECT OF MODIFICATIONS TO AN IN- 
DENTED BODY IN COMBINATION WITH A 45° 
SWEPTBACK WING. Donald L. Loving. September 
1953. 29p. diagrs., photos., tabs. 
(NACA RM L53F02) 



LONGITUDINAL CHARACTERISTICS OF WINGS. 
Thomas A. Toll. October 1953. 18p. diagrs. 
(NACA RM L53I21b) 



DRAG DUE TO LIFT AT MACH NUMBERS UP TO 2.0. 
Edward C. Polhamus. November 1953. 18p. diagrs. 
(NACA RM L53I22b) 



A WIND-TUNNEL INVESTIGATION OF THE USE 
OF SPOILERS FOR OBTAINING STATIC LONGITU- 
DINAL STABILITY OF A CANARD -MISSILE MODEL 
IN REVERSE FLIGHT. Herman S- Fletcher. June 
1954. 15p. diagrs., tab. (NACA RM L54E05) 



THE EFFECT OF CANOPY LOCATION ON THE 
AERODYNAMIC CHARACTERISTICS OF A SWEPT- 
BACK WING-BODY CONFIGURATION AT TRAN- 
SONIC SPEEDS. Harold L. Robinson. June 1954. 
14p. diagrs., photo. (NACA RM L54E11) 



THE ROLLING MOMENT DUE TO SIDESLIP OF 
SWEPT WINGS AT SUBSONIC AND TRANSONIC 
SPEEDS. Edward C. Polhamus and William C . 
S lee man, Jr. March 1955. 81p. diagrs., photos., 
tabs. (NACA RM L54L01) 



COLLECTION AND SUMMARY OF FLAP -TYPE- . 
AILERON ROLLING-EFFECTIVENESS DATA AT 
ZERO LIFT AS DETERMINED BY ROCKET - 
POWERED MODEL TESTS AT MACH NUMBERS 
BETWEEN 0.6 AND 1.6. H. Kurt Strass, Emily W. 
Stephens, E. M. Fields, and Eugene D. Schult. 
September 1955. 95p. diagrs., photos., tabs. 
(NACA RM L55F14) 



EFFECTS OF LEADING-EDGE RADIUS ON THE 
LONGITUDINAL STABILITY OF TWO 45° SWEPT- 
BACK WINGS INCORPORATING LEADING-EDGE 
CAMBER AS INFLUENCED BY REYNOLDS NUM- 
BERS UP TO 8.00 x 10 6 AND MACH NUMBERS UP 
TO 0.290. Gerald V. Foster. October 1955. 44p. 
diagrs. (NACA RM L55H04) 



AERODYNAMICS OF BODIES, WINGS, AND WING- 
BODY COMBINATIONS AT HIGH ANGLES OF AT- 
TACK AND SUPERSONIC SPEEDS. Jack N. 
Nielsen, J. Richard Spahr, and Frank Centolanzi. 
February 1956. 12p. diagrs. (NACA RM A55L13c) 



EFFECTS OF LEADING-EDGE RADIUS ON THE 
LONGITUDINAL STABILITY CHARACTERISTICS OF 
TWO 60O SWEPTBACK WINGS AT HIGH REYNOLDS 
NUMBERS. William C. Schneider. March 1956. 
46p. diagrs. (NACA RM L55L30) 



EFFECTS OF REYNOLDS NUMBER AND LEADING- 
EDGE SHAPE ON THE LOW-SPEED LONGITUDINAL 
STABILITY OF A 6-PERCENT-THICK 45° SWEPT- 
BACK WING. William C. Schneider. April 1956. 
32p. diagrs. (NACA RM L56B14) 



THE VARIATION WITH WING ASPECT RATIO OF 
FLAP EFFECTIVENESS ON THIN RECTANGULAR 
WINGS AT TRANSONIC SPEEDS. John G. Lowry 
and Robert T. Taylor. August 1956. 60p. diagrs., 
tabs. (NACA RM L56E18) 



WIND-TUNNEL INVESTIGATION OF DAMPING IN 
ROLL AT SUPERSONIC SPEEDS OF TRIANGULAR 
WINGS AT ANGLES OF ATTACK. Russell W. 
McDearmon and Robert A. Jones. September 1956. 
32p. diagrs., photos., tab. (NACA RM L56F13a) 



WIND-TUNNEL INVESTIGATION OF THE AERODY- 
NAMIC CHARACTERISTICS OF A SERIES OF 
SWEPT, HIGHLY TAPERED, THIN WINGS AT 
TRANSONIC SPEEDS. TRANSONIC -BUMP METHOD. 
Albert G. Few, Jr., and Paul G. Fournier. January 
1957. 57p. diagrs., photo. (NACA RM L56I24) 



STATIC LONGITUDINAL AND LATERAL STABILITY 
CHARACTERISTICS AT LOW SPEED OF 45° 
SWEPTBACK-MIDWING MODELS HAVING WINGS 
WITH AN ASPECT RATIO OF 2, 4, OR 6. David F. 
Thomas, Jr., and Walter D. Wolhart. September 
1957. 30p. diagrs., photos., tabs. (NACA TN 4077) 



EXPERIMENTAL INVESTIGATION OF LIFT, DRAG, 
AND PITCHING MOMENT OF FIVE ANNULAR AIR- 
FOILS. Hermans. Fletcher. October 1957. 
25p. diagrs., photos. (NACA TN 4117) 



THEORETICAL AND EXPERIMENTAL INVESTIGA- 
TION OF ARBITRARY ASPECT RATIO, SUPER- 
CAVITATING HYDROFOILS OPERATING NEAR THE 
FREE WATER SURFACE. Virgil E. Johnson, Jr. 
December 1957. 94p. diagrs., photos. 
(NACA RM L57I16) 



SOME MEASUREMENTS OF AERODYNAMIC 
FORCES AND MOMENTS AT SUBSONIC SPEEDS 
ON A RECTANGULAR WING OF ASPECT RATIO 2 
OSCILLATING ABOUT THE MIDCHORD. Edward 
Widmayer, Jr., Sherman A. Clevenson, and 
Sumner A. Leadbetter. May 1958. 45p. diagrs., 
tabs. (NACA TN 4240. Supersedes RM L53F19) 



EFFECTS OF BOUNDARY -LAYER DISPLACEMENT 
AND LEADING-EDGE BLUNTNESS ON PRESSURE 
DISTRIBUTION, SKIN FRICTION, AND HEAT TRANS- 
FER OF BODIES AT HYPERSONIC SPEEDS. 
Mitchel H. Bertram and Arthur Henderson, Jr. 
July 1958. 33p. diagrs. (NACA TN 4301) 



SOME FACTORS AFFECTING THE VARIATION OF 
PITCHING MOMENT WITH SIDESLIP OF AIRCRAFT 
CONFIGURATIONS. Edward C. Polhamus. August 
1958. 35p. diagrs., photo. (NACA TN 4016. 
Supersedes RM L55E20b) 



ANALYTICAL AND EXPERIMENTAL INVESTIGA- 
TION OF AERODYNAMIC FORCES AND MOMENTS 
ON LOW -ASPECT-RATIO WINGS UNDERGOING 
FLAPPING OSCILLATIONS. Donald S. Woolston, 
Sherman A. Clevenson, and Sumner A. Leadbetter. 
August 1958. 25p. diagrs., tab. (NACA TN 4302) 



(1) AERODYNAMICS 



39 



STATIC LONGITUDINAL AND LATERAL STABILITY 
CHARACTERISTICS AT LOW SPEED OF 60° 
SWEPTBACK-MIDWING MODELS HAVING WINGS 
WITH AN ASPECT RATIO OF 2, 4, OR 6. Walter D. 
Wolhart and David F. Thomas, Jr. September 1958. 
41p. diagrs., tabs. (NACA TN 4397) 



(1.2.2.2.3) 

Sweep 



AERODYNAMIC STUDY OF A WING-FUSELAGE 
COMBINATION EMPLOYING A WING SWEPT BACK 
630. _ EFFECTS AT SUBSONIC SPEEDS OF A 
CONSTANT-CHORD ELEVON ON A WING CAM- 
BERED AND TWISTED FOR A UNIFORM LOAD AT 
A LIFT COEFFICIENT OF 0.25. J. Ltoyd Jones and 
Fred A. Demele. December 5, 1949. 44p. diagrs., 
photos., tab. (NACA RM A9I27) 



THE EFFECTS OF SCALE AND TEST TECHNIQUE 
ON THE VALIDITY OF SMALL-SCALE MEASURE- 
MENTS OF THE AERODYNAMIC CHARACTERISTICS 
OF A WING WITH THE LEADING EDGE SWEPT 
BACK 63». L . Stewart Rolls. December 9, 1949. 
20p. diagrs., photos. (NACA RM A9J06) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR-ARC SECTIONS AND 40° SWEEPBACK. 
A PRESSURE -DISTRIBUTION STUDY OF THE AERO- 
DYNAMIC CHARACTERISTICS OF THE WING AT 
MACH NUMBER 1.59. Morton Cooper and M. Leroy 
Spearman. May 23, 1950. 52p. diagrs., photos., 
tabs. (NACA RM L50C24) 



A COMPARISON OF THE AERODYNAMIC CHARAC- 
TERISTICS AT TRANSONIC SPEEDS OF FOUR 
WING -FUSELAGE CONFIGURATIONS AS DETER- 
MINED FROM DIFFERENT TEST TECHNIQUES 
Charles J. Donlan, BoydC. Myers. II, and Axel T 
Mattson. October 4, 1950. 66p diagrs , photos , 
tabs. (NACA RM L50H02) 



AN INVESTIGATION OF A SUPI'RSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR-ARC SECTIONS AND 40° SWEEPBACK. 
FORCE CHARACTERISTICS OF THE COMPLETE 
CONFIGURATION AND ITS VARIOUS COMPONENTS 
AT MACH NUMBERS OF 140 AND 1.59. Norman F. 
Smith and Jack E. Marte. January 22. 1951. 55p. 
diagrs., photos., tah. (NACA RM L50K14) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR-ARC SECTION AND 40° SWEEPBACK. 
A PRESSURE-DISTRIBUTION STUDY OF THE AERO- 
DYNAMIC CHARACTERISTICS OF THE WING AT 
MACH NUMBER 1.40. Norman F. Smith, Julian H. 
Kainer, and Robert A. Webster. April 20, 1951. 
48p. diagrs., photos., tabs. (NACA RM L51C06) 



REVIEW OF THE MAXIMUM-LIFT CHARACTER- 
ISTICS OF THIN AND SWEPT WINGS. JolwG. 
Lowry and Jones F. CahiU. June 5, 1951. lOp. 
diagrs. (NACA FM L51E03) 



LIFT, DRAG, -\ND PITCHING MOMENT OF LOW- 
ASPECT -RATIO WINGS AT SUBSONIC AND SUPER- 
SONIC SPEEDS - TWISTED AND CAMBERED TRI- 
ANGULAR WING OF ASPECT RATIO 2 WITH NACA 
0-103- 63 THICKNESS DISTRIBUTION. Charles F. 
Holland John C. Heitmryor. June 12, 1951. 24p. 
:H:igrs.. nhnin., KV). (NACA RVI A51E01) 



BASIC PRESSURE MEASUREMENTS ON A FUSE- 
LAGE AND A 45° SWEPTBACK WING-FUSELAGE 
COMBINATION AT TRANSONIC SPEEDS IN THE 
SLOTTED TEST SECTION OF THE LANGLEY 
8-FOOT HIGH-SPEED TUNNEL. Donald L. Loving 
and Claude V. Williams. September 1951. 59p. 
diagrs., photos. (NACA RM L51F05) 



FREE-FLIGHT MEASUREMENTS AT MACH NUM- 
BERS FROM 0.7 TO 1.6 OF SOME EFFECTS OF 
AIRFOIL-THICKNESS DISTRIBUTION AND 
TRAILING-EDGE ANGLE ON AILERON ROLLING 
EFFECTIVENESS AND DRAG FOR WINGS WITH 0° 
AND 45° SWEEPBACK. E. M. Fields and H. Kurt 
Strass. October 1951. 63p. diagrs., photos., tab. 
(NACA RM L51G27) 



AN INVESTIGATION AT TRANSONIC SPEEDS OF 
THE EFFECTS OF THICKNESS RATIO AND OF 
THICKENED ROOT SECTIONS ON THE AERODY- 
NAMIC CHARACTERISTICS OF WINGS WITH 47° 
SWEEPBACK. ASPECT RATIO 3.5, AND TAPER 
RATIO 0.2 IN THE SLOTTED TEST SECTION OF 
THE LANGLEY 8-FOOT HIGH-SPEED TUNNEL.' 
Ralph P. Bielat, Daniel E. Harrison, and Domenic A. 
Coppolino. October 1951. 38p. diagrs., photo., tab. 
(NACA RM L51I04a) 



AERODYNAMIC CHARACTERISTICS AT SUPER- 
SONIC SPEEDS OF A SERIES OF WING-BODY 
COMBINATIONS HAVING CAMBERED WINGS WITH 
AN ASPECT RATIO OF 3.5 AND A TAPER RATIO 
OF 0.2. EFFECT AT M = 1.60 OF NACELLE 
SHAPE AND POSITION ON THE AERODYNAMIC 
CHARACTERISTICS IN PITCH OF TWO WING-BODY 
COMBINATIONS WITH 47° SWEPTBACK WINGS. 
Lowell E. Hasel and John R. Sevier, Jr. January 
1952. 31p. diagrs., photos., tabs. 
(NACA RM L51K14a) 



AERODYNAMIC CHARACTERISTICS AT SUPER- 
SONIC SPEEDS OF A SERIES OF WING-BODY 
COMBINATIONS HAVING CAMBERED WINGS WITH 
AN ASPECT RATIO OF 3.5 AND A TAPER RATIO OF 
0,2. EFFECTS OF SWEEP ANGLE AND THICKNESS 
RATIO ON THE STATIC LATERAL STABILITY 
CHARACTERISTICS AT M = 1.60. M. Leroy ' 
Spearman and John H. Hilton, Jr. January 1952. 
31p. diagrs., tabs. (NACA RM L51K15a) 



AERODYNAMIC CHARACTERISTICS AT SUPER- 
SONIC SPEEDS OF A SERIES OF WING-BODY 
COMBINATIONS HAVING CAMBERED WINGS WITH 
AN ASPECT RATIO OF 3.5 AND A TAPER RATIO 
OF 0.2. EFFECTS OF SWEEP ANGLE AND THICK- 
NESS RATIO ON THE AERODYNAMIC CHARACTER- 
ISTICS IN PITCH AT M = 1.60. Ross B. Robinson 
and Cornelius Driver. January 1952. 27p. diagrs., 
photos., tabs. (NACA RM L51K16a) 



SUMMARY OF SOME EFFECTIVE AERODYNAMIC 
TWISTING-MOMENT COEFFICIENTS OF VARIOUS 
WING-CONTROL CONFIGURATIONS AT MACH 
NUMBERS FROM 0.6 TO 1.7 AS DETERMINED' 
FROM ROCKET-POWERED MODELS. H- Kurt 
Strass. January 1952. 22p. diagrs., photo., 
2 tabs. (NACA RM L51K20) 



LIFT, DRAG, AND PITCHING MOMENT OF LOW- 
ASPECT-RATIO WTNGS AT SUBSONIC AND SUPER- 
SONIC SPEEDS - TWISTED AND CAMBERED TRI- 
ANGULAR WING OF ASPECT RATIO 2 WITH NACA 
0005-63 THICKNESS DISTRIBUTION. John C. ' 
Heitmeyer and Robert B. Petersen. April 1952. 
20p. diagrs., tabs. (NACA RM A52B08) 



40 



(1) AERODYNAMICS 



AERODYNAMIC LOADING CHARACTERISTICS OF A 
WING-FUSELAGE COMBINATION HAVING A WING 
OF 450 SWEEPBACK MEASURED IN THE LANGLEY 
8 -FOOT TRANSONIC TUNNEL. Donald L- Loving 
andClaudeV. Williams. May 1952. 58p. diagrs., 
photos., tab. (NACA RM L52B27) 



A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE AERODYNAMIC CHARACTERISTICS OF THREE 
4-PERCENT-THICK WINGS OF SWEEPBACK 
ANGLES 10.8°, 350, AND 47°, ASPECT RATIO 3.5, 
AND TAPER RATIO 0.2 rN COMBINATION WITH A 
BODY. Ralph P Biclat. July 1952. 33p. diagrs., 
pnotos., tab. (naca RM lszbuh) 



AERODYNAMIC CHARACTERISTICS AT SUPER- 
SONIC SPEEDS OF A SERIES OF WING-BODY COM- 
BINATIONS HAVING CAMBERED WINGS WITH AN 
ASPECT RATIO OF 3.5 AND A TAPER RATIO OF 
0.2. EFFECTS OF SWEEP ANGLE AND THICKNESS 
RATIO ON THE AERODYNAMIC CHARACTERISTICS 
IN PITCH AT M = 2.01. Ross B. Robinson. July 
1952. 27p. diagrs., photo., tabs. 
(NACA RM L52E09) 



AERODYNAMIC CHARACTERISTICS AT SUPER- 
SONIC SPEEDS OF A SERIES OF WING-BODY COM- 
BINATIONS HAVING CAMBERED WINGS WITH AN 
ASPECT RATIO OF 3.5 AND A TAPER RATIO OF 
0.2. EFFECTS OF SWEEP ANGLE AND THICKNESS 
RATIO ON THE STATIC LATERAL STABILITY 
CHARACTERISTICS AT M = 2.01. Clyde V. 
Hamilton. August 1952. 37p. diagrs., tabs. 
(NACA RM L52E23) 



PRELIMINARY INVESTIGATION OF THE LOW- 
AMPLITUDE DAMPING IN PITCH OF TAILLESS 
DELTA- ANDSWEPT-WING CONFIGURATIONS AT 
MACH NUMBERS FROM 0.7 TO 1.35. Charles T. 
D'Aiutolo and Robert N. Parker. August 1952. 27p. 
diagrs., photos., tab. (NACA RM L52G09) 



A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF NACELLE SHAPE AND POSITION 
ON THE AERODYNAMIC CHARACTERISTICS OF 
TWO 470 SWEPTBACK WING-BODY CONFIGURA- 
TIONS. Ralph P. Bielat and Daniel E. Harrison. 
September 1952. 87p. diagrs., photos., tab. 
(NACA RM L52G02) 



LOW-SPEED STATIC LONGITUDINAL AND LAT- 
ERAL STABILITY CHARACTERISTICS OF A MODEL 
WITH LEADING-EDGE CHORD-EXTENSIONS INCOR- 
PORATED ON A 40O SWEPTBACK CIRCULAR-ARC 
WING OF ASPECT RATIO 4 AND TAPER RATIO 0.50. 
Kenneth W. Goodson and Albert G. Few, Jr. 
November 1952. 46p. diagrs., photos., tab. 
(NACA RM L52I18) 



AERODYNAMIC CHARACTERISTICS EXTENDED TO 
HIGH ANGLES OF ATTACK AT TRANSONIC SPEEDS 
OF A SMALL-SCALE 0° SWEEP WING, 45<> SWEPT- 
BACK WING, AND 60° DELTA WING. Harleth G. 
Wiley. November 1952. 26p. diagrs. 
(NACA RM L52I30) 



EFFECT OF LEADING-EDGE CHORD-EXTENSIONS 
ON SUBSONIC AND TRANSONIC AERODYNAMIC 
CHARACTERISTICS OF THREE MODELS HAVING 
45° SWEPTBACK WINGS OF ASPECT RATIO 4. 

Kenneth W. Goodson and Albert G. Few, Jr. 
January 1953. 31p. diagrs., photos., tab. 
(NACA RM L52K21) 



SOME MEASUREMENTS OF FLYING QUALITIES OF 
A DOUGLAS D-558-H RESEARCH AIRPLANE DUR- 
ING FLIGHTS TO SUPERSONIC SPEEDS. Herman O. 
Ankenbruck and Theodore E. Dahlen. March 1953. 
25p. diagrs., photos., tab. (NACA RM L53A06) 



LIFT, DRAG, AND PITCHING MOMENT OF LOW- 
ASPECT-RATIO WINGS AT SUBSONIC AND SUPER- 
SONIC SPEEDS. Charles F. Hall. April 1953. 
132p. diagrs., tabs. (NACA RM A53A30) 



COMPARISON OF THE AERODYNAMIC CHARACTER- 
ISTICS AT TRANSONIC SPEEDS OF A PLANE WING 
AND A CAMBERED AND TWISTED WING, BOTH 
HAVING 45° OF SWEEPBACK AND AN ASPECT 
RATIO OF 6. George H. Holdaway. May 1953. 
49p. diagrs., photos. (NACA RM A53B16) 



LOADS DUE TO FLAPS AND SPOILERS ON SWEPT- 
BACK WINGS AT SUPERSONIC AND TRANSONIC 
SPEEDS. Alexander D. Hammond and F E. West. 
Jr. June 1953. 17p. diagrs. (NACA RM L53D29a) 



THE INFLUENCE OF A CHANGE IN BODY SHAPE 
ON THE EFFECTS OF TWIST AND CAMBER AS 
DETERMINED BY A TRANSONIC WIND-TUNNEL 
INVESTIGATION OF A 45° SWEPTBACK WING- 
FUSELAGE CONFIGURATION. Daniel E. Harrison. 
August 1953. 23p. diagrs., tab. 
(NACA RM L53B03) 



INVESTIGATION OF WING FLUTTER AT TRAN- 
SONIC SPEEDS FOR SDC SYSTEMATICALLY VARIED 
WING PLAN FORMS. George W. Jones, Jr., and 
Hugh C. DuBose. August 1953. 32p. diagi*., 
photos., 3 tabs. (NACA RM L53G10a) 



NOTES ON DAMPING IN ROLL AND LOAD DISTRI- 
BUTIONS IN ROLL AT HIGH ANGLES OF ATTACK 
AND HIGH SUBSONIC SPEED. Richard E\ Kuhn. 
August 1953. 18p. diagrs., tab. 
(NACA RM L53G13a) 



A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECT OF MODIFICATIONS TO AN IN- 
DENTED BODY IN COMBINATION WITH A 45° 
SWEPTBACK WING. Donald L. Loving. September 
1953. 29p. diagrs., photos., tabs. 
(NACA RM L53F02) 



INVESTIGATION OF SPOILER AILERONS WITH AND 
WITHOUT A GAP BEHIND THE SPOILER ON A 45° 
SWEPTBACK WING-FUSELAGE COMBINATION AT 
MACH NUMBERS FROM 0.60 TO 1.03. F. E. West, 
Jr., William Solomon, and Edward M. Brummal. 
September 1953. 38p. diagrs. (NACA RM L53G07a) 



INVESTIGATION OF THE EFFECT OF SPANWISE 
POSITIONING OF A VERTICALLY SYMMETRIC 
OGIVE -CYLINDER NACELLE ON THE HIGH-SPEED 
AERODYNAMIC CHARACTERISTICS OF A 45° 
SWEPTBACK TAPERED-IN-THTCKNESS WING OF 
ASPECT RATIO 6 WITH AND WITHOUT A FUSE- 
LAGE. H. Norman Silvers and Thomas J. King, Jr. 
October 1953. 62p. diagrs., tabs. 
(NACA RM L53H17) 



41 



(1) AERODYNAMICS 



ROCKET-MODEL INVESTIGATION TO DETERMINE 
THE HINGE-MOMENT AND NORMAL-FORCE 
PROPERTIES OF A FULL-SPAN, CONSTANT- 
CHORD, PARTIALLY BALANCED TRAILING -EDGE 
CONTROL ON A 60° CLIPPED DELTA WING BE- 
TWEEN MACH NUMBERS OF 0.50 AND 1.26. 
C. William Martz and John W. Goslee. October 
1953. 3 3 p. diagrs., photos., tab. 
(NACA RM L53I04) 



LONGITUDINAL CHARACTERISTICS OF WINGS. 
Thomas A. Toll. October 1953. 18p. diagrs. 
(NACA RM L53I21b) 



DATA ON SPOILER-TYPE AILERONS. 
Lowry. October 1953. 27p. diagrs. 
(NACA RM L53I24a) 



John G. 



A STUDY OF THE USE OF LEADING-EDGE 
NOTCHES AS A MEANS FOR IMPROVING THE LOW- 
SPEED PITCHTNG-MOMENT CHARACTERISTICS OF 
A THIN 450 SWEPT WING OF ASPECT RATIO 4. 
Joseph Weil and William D. Morrison, Jr. 
December 1953. 17p. diagrs. (NACA RM L53j27a) 



LONGITUDINAL STABILITY CHARACTERISTICS 
AT TRANSONIC SPEEDS OF A ROCKET- 
PROPELLED MODEL OF AN AIRPLANE CON- 
FIGURATION HAVING A 450 SWEPT WING OF 
ASPECT RATIO 6.0. John C. McFall, Jr. 
January 1954. 34 p. diagrs,, photos. 
(NACA RM L53G22a) 



WIND-TUNNEL INVESTIGATIONS AT LOW AND 
TRANSONIC SPEEDS OF THE FEASIBILITY OF 
SELF-ACTUATING SPOILERS AS A LATERAL- 
CONTROL DEVICE FOR A MISSILE. Harleth G. 
Wiley and William C. Hayes, Jr. January 1954. 
24 p. diagrs., tab. (NACA RM L53K27) 



WIND-TUNNEL INVESTIGATION AT HIGH SUBSONIC 
SPEEDS OF THE EFFECTS OF WING -MOUNTED 
EXTERNAL STORES ON THE LOADING AND AERO- 
DYNAMIC CHARACTERISTICS IN PITCH OF A 45° 
SWEPTBACK WING COMBINED WITH A FUSELAGE. 
H. Norman Silvers, Thomas J. King, Jr., and 
William J. Alford, Jr. March 1954. 36p. diagrs., 
tabs. (NACA RM L54A21) 



THE EFFECT OF A CHANGE IN BODY SHAPE ON 
THE LOADING OF A 45° SWEPTBACK WING-BODY 
COMBINATION AT TRANSONIC SPEEDS. Donald L. 
Loving. April 1954. 67p. diagrs., photo. 
(NACA RM L54B09) 



INVESTIGATION AT HIGH SUBSONIC SPEEDS OF 
FINNED AND UNFINNED BODIES MOUNTED AT 
VARIOUS LOCATIONS FROM THE WINGS OF UN- 
SWEPT, AND SWEPT -WING-FUSELAGE MODELS, 
INCLUDING MEASUREMENTS OF BODY LOADS. 
William J. Alford, Jr., and H. Norman Silvers. 
April 1954. 93p. diagrs., photos., tabs. 
(NACA RM L54B18) 



EFFECTS OF SPOILER AILERONS ON THE AERO- 
DYNAMIC LOAD DISTRIBUTION OVER A 45° 
SWEPTBACK WING AT MACH NUMBERS FROM 0.60 
TO 1.03. Joseph M. Hallissy, Jr., F. E. West, Jr., 
and George Liner. May 1954. I62p. diagrs., tabs. 
(NACARM L54C17a) 



INVESTIGATION AT HIGH SUBSONIC SPEEDS OF 
THE EFFECT OF ADDING VARIOUS COMBINATIONS 
OF MISSILES ON THE AERODYNAMIC CHARACTER- 
ISTICS OF SWEPTBACK AND UNSWEPT WINGS 
COMBINED WITH A FUSELAGE. H. Norman 
Silvers and William J. Alford, Jr. June 1954. 39p. 
diagrs., photo., tabs. (NACA RM L54D20) 



THE EFFECT OF CANOPY LOCATION ON THE 
AERODYNAMIC CHARACTERISTICS OF A SWEPT- 
BACK WING-BODY CONFIGURATION AT TRAN- 
SONIC SPEEDS. Harold L. Robinson. June 1954. 
14p. diagrs., photo. (NACA RM L54E11) 



INVESTIGATION OF THE EFFECT OF INDENTATION 
ON AN M-PLAN-FORM-WING-BODY COMBINATION 
AT TRANSONIC SPEEDS. Donald L. Loving. 
August 1954. 24p. diagrs., photos., tab. 
(NACA RM L54F14) 



LOW -SPEED MEASUREMENT OF STATIC STABIL- 
ITY AND DAMPING DERIVATIVES OF A 60° 
DELTA-WING MODEL FOR ANGLES OF ATTACK 
OF 0O TO 90°. Donald E. Hewes. September 1954. 
30p. diagrs., photo., tab. (NACA RM L54G22a) 



ANALYTICAL STUDY OF THE EFFECT OF 
CENTER-OF-GRAVITY POSITION ON THE RE- 
SPONSE TO LONGITUDINAL CONTROL IN LANDING 
APPROACHES OF A SWEPT -WING A1KPLAN& Or 
LOW ASPECT RATIO HAVING NO HORIZONTAL 
TAIL. Ralph W. Stone, Jr. October 1954. 35p. 
diagrs., tabs. (NACA RM L54H04) 



FREE -FLIGHT MEASUREMENTS OF THE ROLLING 
EFFECTIVENESS AND OPERATING CHARACTER- 
ISTICS OF A BELLOWS-ACTUATED SPLIT-FLAP 
AILERON ON A 60<> DELTA WING AT MACH NUM- 
BERS BETWEEN 0.8 AND 1.8. Eugene D. Schult. 
October 1954. 33p. diagrs., photos. 
(NACA RM L54H17) 



AN INVESTIGATION OF THE EFFECTS OF A GEO- 
METRIC TWIST ON THE AERODYNAMIC LOADING 
CHARACTERISTICS OF A 45° SWEPTBACK WING- 
BODY CONFIGURATION AT TRANSONIC SPEEDS. 
Claude V. Williams. October 1954. 87p. diagrs.. 
photos., tabs. (NACA RM L54H18) 



PRELIMINARY LOW-SPEED WIND-TUNNEL INVES- 
TIGATION OF SOME ASPECTS OF THE AERODY- 
NAMIC PROBLEMS ASSOCIATED WITH MISSILES 
CARRIED EXTERNALLY IN POSTTK)NS NEAR AIR- 
PLANE WINGS. William J. Alford, Jr., H. Norman 
Silvers, and Thomas J. King, Jr. December 1954. 
30p. diagrs., photos., tab. (NACA RM L54J20) 



EFFECTS OF INCREASING REYNOLDS NUMBER 
FROM 2 x 10 6 TO 6 x 106 ON THE AERODYNAMIC 
CHARACTERISTICS AT TRANSONIC SPEEDS OF A 
45° SWEPT WING WITH 6° LEADING-EDGE DROOP. 
James W. Schmeer and J. Lawrence Cooper. 
February 1955. 22p. diagrs., photo. 
(NACA RM L54L10) 



EFFECTS OF SWEEP AND TAPER RATIO ON THE 
LONGITUDINAL CHARACTERISTICS OF AN ASPECT 
RATIO 3 WING-BODY COMBINATION AT MACH 
NUMBERS FROM 0.6 TO 1.4. Earl D. Knechtel and 
James L. Summers. March 1955. 36p. diagrs., 
photo. (NACA RM A55A03) 



42 



(1) AERODYNAMICS 



THE ROLLING MOMENT- DUE TO SIDESLIP OF 
SWEPT WINGS AT SUBSONIC AND TRANSONIC 
SPEEDS. Edward C Polhamus and William C. 
Sleeman, Jr. March 1955. 81p. diagrs., photos., 
tabs. (NACA RM L54L01) 



TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF SWEEPBACK AND THICKNESS 
RATIO ON THE WING LOADS OF A WING-BODY 
COMBINATION OF ASPECT RATIO 4 AND TAPER 
RATIO 0.6. Robert J. Piatt, Jr., and Joseph D- 
Brooks. April 1955. 44p. diagrs., photos., tab. 
{NACA RM L54L31b) 



COMPARISON OF THE STATIC STABILITY OF A 
68.7° DELTA-WING MODEL WITH DIHEDRAL AND 
A TWISTED AND CAMBERED WING MODEL OF THE 
SAME PLAN FORM. John W. Paulson. April 1955. 
18p. diagrs., tab. (NACA RM L55BU) 



EFFECT OF A WING LEADING-EDGE FLAP AND 
CHORD-EXTENSION ON THE HIGH SUBSONIC 
CONTROL CHARACTERISTICS OF AN AILERON 
LOCATED AT TWO SPANWISE POSITIONS. Robert 
F. Thompson and Robert T. Taylor. May 1955. 
59p. diagrs,, photo., tabs. (NACA RM L55B18a) 



A COMPARISON AT MACH NUMBERS UP TO 0.92 
OF THE CALCULATED AND EXPERIMENTAL 
DOWNWASH AND WAKE CHARACTERISTICS AT 
VARIOUS HORIZONTAL TAIL HEIGHTS BEHIND A 
WING WITH 450 OF SWEEPBACK. Jack D. 
Stephenson, Ralph Selan, and Angelo Bandettini. 
June 1955. 81p. diagrs., photos., tabs. 
(NACA RM A55D27a) 



COLLECTION AND SUMMARY OF FLAP -TYPE - 
AILERON ROLLING -EFFECTIVENESS DATA AT 
ZERO LIFT AS DETERMINED BY ROCKET- ( 
POWERED MODEL TESTS AT MACH NUMBERS 
BETWEEN 0.6 AND 1.6. H. Kurt Strass, Emily W. 
Stephens, E. M. Fields, and Eugene D. Schult. 
September 1955. 95p. diagrs., photos., tabs. 
(NACA RM L55F14) 



EFFECT OF LEADING-EDGE SWEEPBACK ON LIFT, 
DRAG, AND PITCHING-MOMENT CHARACTERIS- 
TICS OF THIN WINGS OF ASPECT RATIO 3 AND 
TAPER RATIO 0.4 AT SUBSONIC AND SUPERSONIC 
SPEEDS. Benton E. Wetzel. November 1955. 22p. 
diagrs., tabs. (NACA RM A55H04a) 



THE EFFECT OF LEADING-EDGE DROOP UPON 
THE PRESSURE DISTRIBUTION AND AERODYNAM- 
IC LOADING CHARACTERISTICS OF A 45° SWEPT- 
BACK WING AT TRANSONIC SPEEDS. James W. 
Schmeer. November 1955. 42p. diagrs., photos. 
(NACA RM L55I16) 



INVESTIGATION AT HIGH SUBSONIC SPEEDS OF 
THE STATIC LONGITUDINAL STABILITY CHARAC- 
TERISTICS OF A MODEL HAVING CROPPED-DELTA 
AND UNSWEPT WING PLAN FORMS AND SEVERAL 
TAIL CONFIGURATIONS. Albert G. Few, Jr. 
November 1955. 107p. diagrs., photo., tab. 
(NACA RM L55I23a) 



LOW -SPEED PRESSURE-DISTRIBUTION INVESTI- 
GATION OF A SPOILER AND A SPOILER -SLOT- 
DEFLECTOR ON A 30° SWEPTBACK WING- 
FUSELAGE MODEL HAVING AN ASPECT RATIO 
OF 3, A TAPER RATIO OF 0.5, AND NACA 65A004 
AIRFOIL SECTION. Alexander D. Hammond. 
January 1956. 176p. diagrs., tabs. 
(NACA RM L55I29) 



SOME EFFECTS OF SWEEP AND THICKNESS ON 
THE EXPERIMENTAL DOWNWASH CHARACTER- 
ISTICS AT TRANSONIC SPEEDS OF A SERIES OF 
HIGHLY TAPERED WINGS WITH AN ASPECT RATIO 
OF 3. TRANSONIC -BUMP METHOD. Albert G. 
Few, Jr. February 1956. 65p. diagrs., photo. 
(NACARML55J12^ 



PRELIMINARY FREE -FLIGHT STUDY OF THE 
DRAG AND STABILITY OF A SERIES OF SHORT- 
SPAN MISSILES AT MACH NUMBERS FROM 0.9 TO 
1.3. James Rudyard Hall. February 1956. 14p. 



HlafrB nhoto. 'NACA RM L5RJ13) 



EXPERIMENTAL INVESTIGATION AT HIGH SUB- 
SONIC SPEED OF THE ROLLING STABILITY 
DERIVATIVES OF A COMPLETE MODEL HAVING 
A CLIPPED-DELTA WING AND A HIGH HORIZON- 
TAL TAIL. William C. Sleeman, Jr., and Albert G. 
Few, Jr. February 1956. 32p. diagrs., tab. 
(NACA RM L55K11) 



LONGITUDINAL STABILITY INVESTIGATION FOR 
A MACH NUMBER RANGE OF 0.8 TO 1.7 OF AN 
AIRPLANE CONFIGURATION WITH A 45° SWEPT 
WING AND A LOW HORIZONTAL TAIL- John C 
McFall, Jr. February 1956. 32p. diagrs., photos., 
tab. (NACA RM L55L09) 



SOME EFFECTS OF AILERONS ON THE VARIATION 
OF AERODYNAMIC CHARACTERISTICS WITH SIDE- 
SLIP AT LOW SPEED. Kenneth W- Goodson. 
March 1956. 40p. diagrs., tab. (NACA RM L55L20) 



LOW-SPEED INVESTIGATION OF THE EFFECTS 
OF WING DIHEDRAL ANGLE AND FIN LENGTH ON 
THE STATIC STABILITY CHARACTERISTICS OF A 
MODEL HAVING AN 82° DELTA WING. Kenneth P. 
Spreemann. April 1956. 30p. diagrs. 
(NACA RM L55L30a) 



LOW -SPEED MEASUREMENTS OF STATIC STABIL- 
ITY, DAMPING IN YAW, AND DAMPING IN ROLL 
OF A DELTA, A SWEPT. AND AN UNSWEPT WING 
FOR ANGLES OF ATTACK FROM 0° TO 90°. 
Joseph L. Johnson, Jr. April 1956. 19 p. diagrs., 
tabs. (NACA RM L56B01) 



INVESTIGATION AT HIGH SUBSONIC SPEEDS OF 
THE EFFECT OF HORIZONTAL -TAIL LOCATION 
ON LONGITUDINAL AND LATERAL STABILITY 
CHARACTERISTICS OF A COMPLETE MODEL 
HAVING A SWEPTBACK WING IN A HIGH LOCA- 
TION. H. Norman Silvers and Thomas J . King, Jr. 
April 1956. 46p. diagrs., tab. (NACA RM L56B10) 



HEAT REQUIREMENTS FOR ICE PROTECTION OF 
A CYCLICALLY GAS-HEATED, 36° SWEPT AIR- 
FOIL WITH PARTIAL-SPAN LEADING-EDGE SLAT. 
Vernon H. Gray and Uwe H. von Glahn. May 1956. 
73p. diagrs., photos., tabs. (NACA RM E56B23) 



INVESTIGATION OF THE USE OF AREA SUCTION 
TO INCREASE THE EFFECTIVENESS OF 
TRAILING-EDGE FLAPS OF VARIOUS SPANS ON 
A WING OF 45° SWEEPBACK AND ASPECT RATIO 
6. Roy N. Griffin, Jr., and David H. Hickey. 
June 1956. 64 p. diagrs., photo., tabs. 
(NACA RM A56B27) 



( 1 ) AERODYNAMICS 



43 



LOW-SPEED WIND-TUNNEL RESULTS FOR A THIN 
ASPECT-RATIO- 1. 85 POINTED-WING-FUSELAGE 
MODEL WITH DOUBLE SLOTTED FLAPS. Albert 
E Brown. July 1956. 31p. diagrs.., tabs. 
(NACA RM L56D03) 



SOME EFFECTS OF WING FENCES ON THE LATER- 
AL STABILITY DERIVATIVES OF A 60° DELTA 
WING OSCILLATING CONTINUOUSLY IN YAW. 
Donald R. Riley. July 1956. 29p. diagrs., photos., 
tab. (NACA RM L56D13) 



HINGE MOMENT AND EFFECTIVENESS OF AN 
UNSWEPT CONSTANT -CHORD CONTROL AND AN 
OVERHANG-BALANCED, SWEPT HINGE-LINE 
CONTROL ON AN 80° SWEPT POINTED WING AT 
MACH NUMBERS FROM 0.75 TO 1.96. Lawrence D. 
Guy. August 1956. 39p. diagrs., photo. 
(NACA RM L56F11) 



LOW-SPEED INVESTIGATION OF THE LATERAL- 
CONTROL CHARACTERISTICS OF A FLAP-TYPE 
SPOILER AND A SPOILER-SLOT-DEFLECTOR ON 
A 30° SWEPTBACK WING-FUSELAGE MODEL 
HAVING AN ASPECT RATIO OF 3, A TAPER RATIO 
OF 0.5. AND NACA 65A004 AIRFOIL SECTION. 
Alexander D. Hammond. August 1956. 25p. diagrs., 
tab. (NACA RM L56F18) 



APPLICATION OF AREA SUCTION TO LEADING- 
EDGE AND TRAILING-EDGE FLAPS ON A 44° 
SWEPT -WING MODEL. Curt A. Holzhauser, Robert 
K. Martin, andV. Robert Page. September 1956. 
66p. diagrs., photos., tabs. (NACA RM A56F01) 



WIND-TUNNEL INVESTIGATION OF DAMPING IN 
ROLL AT SUPERSONIC SPEEDS OF TRIANGULAR 
WINGS AT ANGLES OF ATTACK. Russell W. 
McDearmon and Robert A. Jones. September 1956. 
32p. diagrs., photos., tab. (NACA RM L56F13a) 



INVESTIGATION OF SPOILER-SLOT-DEFLECTOR 
AILERONS AND OTHER SPOILER AILERONS ON A 
45° SWEPTBACK-WING-FUSELAGE COMBINATION 
AT MACH NUMBERS FROM 0.60 TO 1.03. F. E. 
West, Jr.. Charles F. Whitcomb, and James W. 
Schmeer. September 1956. 59p. diagrs., tab. 
(NACA RM L56F15) 



EFFECT OF A FUSELAGE ON THE LOW -SPEED 
LONGITUDINAL AERODYNAMIC CHARACTERISTICS 
OF A 45° SWEPTBACK WING WITH DOUBLE 
SLOTTED FLAPS. Rodger L. Naeseth. September 
1956. 31 p. diagrs., tabs. (NACA RM L56G02) 



STATIC STABILITY CHARACTERISTICS OF A 
CAMBERED-DELTA-WING MODEL AT HIGH 
SUBSONIC SPEEDS. William C. Mosetey, Jr. 
October 1956. 35p. diagrs., photos. 
(NACA RM L56H13) 



A LOW -SPEED INVESTIGATION OF A HIGH-LIFT 
LATERAL-CONTROL DEVICE CONSISTING OF A 
SPOILER-SLOT-DEFLECTOR AND A TRAILING- 
EDGE FLAP ON A TAPERED 45° SWEPTBACK 
WING. Alexander D. Hammond and Jarrett K. 
Huffman. October 1956. 21p. diagrs. 
(NACA RM L56H31) 



LARGE-SCALE WIND-TUNNEL TESTS OF AN AIR- 
PLANE MODEL WITH A 450 SWEPTBACK WING OF 
ASPECT RATIO 2.8 WITH AREA SUCTION APPLIED 
TO TRAILING-EDGE FLAPS AND WITH SEVERAL 
WING LEADING-EDGE MODIFICATIONS. David G 
Koenig and Kiyoshi Aoyagi. November 1956. 66p. 
diagrs., photo., tabs. (NACA RM A56H08) 



LOW -SPEED PRESSURE-DISTRIBUTION INVESTI- 
GATION OF A THIN-DELTA-WING-FUSELAGE 
MODEL WITH DOUBLE SLOTTED FLAP, EX- 
TENDED DOUBLE SLOTTED FLAP, AND CANARD. 
Delwin R. Croom and Jarrett K. Huffman. November 
1956. 104p. diagrs., tabs. (NACA RM L56I11) 



THEORETICAL AND EXPERIMENTAL INVESTIGA- 
TION OF THE SUBSONIC-FLOW FIELDS BENEATH 
SWEPT AND UNSWEPT WINGS WITH TABLES OF 
VORTEX -INDUCED VELOCITIES. William J. 
Alford, Jr. 1957. ii, 43p. diagrs., photo., tabs. 
(NACA Rept. 1327. Supersedes TN 3738) 



WIND-TUNNEL INVESTIGATION OF THE AERODY- 
NAMIC CHARACTERISTICS OF A SERIES OF 
SWEPT, HIGHLY TAPERED, THIN WINGS AT 
TRANSONIC SPEEDS. TRANSONIC-BUMP METHOD. 
Albert G. Few, Jr., and Paul G. Fournier. January 
1957. 57p. diagrs., photo. (NACA RM L56I24) 



STATIC LONGITUDINAL CHARACTERISTICS AT 
HIGH SUBSONIC SPEEDS OF A COMPLETE AIR- 
PLANE MODEL WITH A HIGHLY TAPERED WING 
HAVING THE 0.80 CHORD LINE UNSWEPT AND 
WITH SEVERAL TAIL CONFIGURATIONS. Kenneth 
W. Goodson. January 1957. 57p. diagrs., photo., 
tabs. (NACA RM L56J03) 



EXPERIMENTAL DETERMINATION AT SUBSONIC 
SPEEDS OF THE OSCILLATORY AND STATIC 
LATERAL STABILITY DERIVATIVES OF A SERIES 
OF DELTA WINGS WITH LEADING-EDGE SWEEP 
FROM 30° TO 86.5°. William Letko. April 1957. 
38p. diagrs., photos., tab. (NACA RM L57A30) 



EFFECT OF SWEEP ON PERFORMANCE OF COM- 
PRESSOR BLADE SECTIONS AS INDICATED BY 
SWEPT-BLADE ROTOR, UNSWEPT-BLADE 
ROTOR, AND CASCADE TESTS. William R. 
Godwin. July 1957. 43p. diagrs. (NACA TN 4062) 



STATIC LONGITUDINAL AND LATERAL STABILITY 
CHARACTERISTICS AT LOW SPEED OF 45° 
SWEPTBACK-MIDWING MODELS HAVING WINGS 
WITH AN ASPECT RATIO OF 2, 4, OR 6. David F. 
Thomas, Jr., and Walter D. Wolhart. September 
1957. 30p. diagrs., photos., tabs. (NACA TN 4077) 



WIND-TUNNEL INVESTIGATION OF EFFECTS OF 
GROUND PROXIMITY AND OF SPLIT FLAPS ON 
THE LATERAL STABILITY DERIVATIVES OF A 60° 
DELTA-WING MODEL OSCILLATING IN YAW. 
Byron M. Jaquet. September 1957. 32p. diagrs. 
photos., tab. (NACA TN 4119) 



WIND-TUNNEL INVESTIGATION OF THE STATIC 
LATERAL STABILITY CHARACTERISTICS OF 
WING-FUSELAGE COMBINATIONS AT HIGH SUB- 
SONIC SPEEDS. TAPER-RATIO SERIES. James 
W. Wiggins and Paul G. Fournier. October 1957. 
25p. diagrs., photos. (NACA TN 4174. Supersedes 
RM L53B25a) 



44 



(1) AERODYNAMICS 



THE USE OF A LEADING-EDGE AREA-SUCTION 
FLAP AND LEADING- EDGE MODIFICATIONS TO 
IMPROVE THE HIGH-LIFT CHARACTERISTICS OF 
AN AIRPLANE MODEL WITH A WTNG OF 450 
SWEEP AND ASPECT RATIO 2.8. David G- Koenig 
andKlyoshi Aoyagi. November 1957. 46p. diagrs., 
photo., tabs. (NACA RM A57H21) 



INVESTIGATION OF DEFLECTORS AS GUST ALLE- 
VIATORS ON A 0.09-SCALE MODEL OF THE BELL 
X-5 AIRPLANE WITH VARIOUS WING SWEEP 
ANGLES FROM 20° TO 60© AT MACH NUMBERS 
FROM 0.40 TO 0.90. Delwin R. Croom and Jarrett 
K. Huffman. November 1957. 28p. diagrs. 
(NACA TN 4175) 



WIND-TUNNEL INVESTIGATION OF EFFECT OF 
SWEEP ON ROLLING DERIVATIVES AT ANGLES OF 
ATTACK UP TO 13° AND AT HIGH SUBSONIC MACH 
NUMBERS, INCLUDING A SEMIEMPIRICAL 
METHOD OF ESTIMATING THE ROLLING DERIVA- 
TIVES. James W. Wiggins. January 1958. 47p. 
diagrs., tab. (NACA TN 4185. Supersedes 
RM L54C26) 



STAGNATION-POINT HEAT TRANSFER TO BLUNT 
SHAPES IN HYPERSONIC FLIGHT, INCLUDING 
EFFECTS OF YAW. A. J- Eggers, Jr., 
C. Frederick Hansen, and Bernard E. Cunningham. 
April 1958. 54p. diagr. (NACA TN 4229) 



EFFECTS OF BOUNDARY-LAYER DISPLACEMENT 
AND LEADING-EDGE BLUNTNESS ON PRESSURE 
DISTRIBUTION, SKIN FRICTION, AND HEAT TRANS- 
FER OF BODIES AT HYPERSONIC SPEEDS. 
Mitchel H. Bertram and Arthur Henderson, Jr. 
July 1958. 33p. diagrs. (NACA TN 4301) 



WIND-TUNNEL INVESTIGATION OF THE HIGH- 
SUBSONIC STATIC LONGITUDINAL STABILITY 
CHARACTERISTICS OF SEVERAL WING-BODY CON- 
FIGURATIONS DESIGNED FOR HIGH LIFT-DRAG 
RATIOS AT A MACH NUMBER OF 1.4. Paul G. 
Fournier. July 1958. 42p. diagrs., photo., tab. 
(NACA TN 4340) 



LOW -SPEED EXPERIMENTAL DETERMINATION OF 
THE EFFECTS OF LEADING-EDGE RADIUS AND 
PROFILE THICKNESS ON STATIC AND OSCILLA- 
TORY LATERAL STABILITY DERIVATIVES FOR A 
DELTA WING WITH 60° OF LEADING-EDGE SWEEP. 
Hermans. Fletcher. July 1958. 45p. diagrs., 
photos., tabs. (NACA TN 4341) 



SOME FACTORS AFFECTING THE VARIATION OF 
PITCHING MOMENT WITH SIDESLIP OF AIRCRAFT 
CONFIGURATIONS. Edward C. Polhamus. August 
1958. 35p. diagrs., photo. (NACA TN 4016. 
Supersedes RM L55E20b) 



INVESTIGATION OF MINIMUM DRAG AND MAXI- 
MUM LIFT-DRAG RATIOS OF SEVERAL WING-BODY 
COMBINATIONS INCLUDING A CAMBERED TRI- 
ANGULA?. WTNG AT LOW REYNOLDS NUMBERS 
AND AT SUPERSONIC SPEEDS. Clinton E. Brown 
andL. K. Hargrave. September 1958. 62p. diagrs., 
photos., tabs. (NACA TN 4020. Supersedes 
RM L51E11) 



SIMILAR SOLUTIONS FOR THE COMPRESSIBLE 
BOUNDARY LAYER ON A YAWED CYLINDER WITH 
TRANSPIRATION COOLING. Ivan E. Beckwith. 
September 1958. 72p. diagrs., tabs. 
(NACA TN 4345) 



EFFECTS OF FREQUENCY AND AMPLITUDE ON 
THE YAWING DERr/ATIVES OF TRIANGULAR, 
SWEPT, AND UNSWEPT WINGS AND OF A 
TRIANGULAR-WING-FUSELAGE COMBINATION 
WITH \ND WITHOUT A TRIANGULAR TAIL PER- 
FORMING SINUSOIDAL YAWING OSCILLATIONS. 
William Letko and Herman S. Fletcher. September 
1958. 52p. diagrs., photos., tabs. (NACA TN 4390) 



STATIC LONGITUDINAL AND LATERAL STABILITY 
CHARACTERISTICS AT LOW SPEED OF 60° 
SWEPTBACK-MIDWING MODELS HAVING WINGS 
WITH AN ASPECT RATIO OF ?, ^ OR fi Walter D. 
Wolhart and David F. Thomas, Jr. September 1958. 
41p. diagrs., tabs. (NACA TN 4397) 



(1.2.2.2.4) 
Taper and Twist 



COMPARISON OF THE AERODYNAMIC CHARACTER- 
ISTICS AT TRANSONIC SPEEDS OF A PLANE WING 
AND A CAMBERED AND TWISTED WING, BOTH 
HAVING 45° OF SWEEPBACK AND AN ASPECT 
RATIO OF 6. George H. Holdaway. May 1953. 
49p. diagrs., photos. (NACA RM A53B16) 



LONGITUDINAL CHARACTERISTICS OF WINGS. 

Thomas A. Toll. October 1953. 18p. diagrs. 
(NACA RM L53I21b) 



DRAG DUE TO LIFT AT MACH NUMBERS UP TO 2.0. 
Edward C. Polhamus. November 1953. 18p. diagrs. 
(NACA RM L53I22b) 



TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF TAPER RATIO, BODY INDEN- 
TATION, FDCED TRANSITION, AND AFTERBODY 
SHAPE ON THE AERODYNAMIC CHARACTERIS- 
TICS OF A 45° SWEPTBACK WING-BODY COMBI- 
NATION. Francis G. Morgan, Jr., and Melvin M. 
Carmel. March 1954. 37p. diagrs., tab. 
(NACA RM L54A15) 



AN INVESTIGATION OF THE EFFECTS OF A GEO- 
METRIC TWIST ON THE AERODYNAMIC LOADRJG 
CHARACTERISTICS OF A 45° SWEPTBACK WING- 
BODY CONFIGURATION AT TRANSONIC SPEEDS. 
Claude V. Williams. October 1954. 87p. diagrs., 
photos., tabs. (NACA RM L54H18) 



EFFECT OF TAPER RATIO ON LIFT, DRAG, AND 
PITCHING-MOMENT CHARACTERISTICS OF THIN 
WINGS OF ASPECT RATIO 3 WITH 53.1° SWEEP- 
BACK OF LEADING EDGE AT SUBSONIC AND 
SUPERSONIC SPEEDS. Benton E. Wetzel. 
January 1955. 25p. diagrs., photo., tabs. 
(NACA RM A54J20) 



EFFECTS OF TAPER RATIO ON THE LONGITUDI- 
NAL CHARACTERISTICS AT MACH NUMBERS 
FROM 0.6 TO 1.4 OF A WING-BODY-TAIL COMBI- 
NATION HAVING AN UNSWEPT WING OF ASPECT 
RATIO 3. James L. Summers, Stuart L. Treon, 
and Lawrence A. Graham. March 1955. 45p. - 
diagrs., photo. (NACA RM A54L20) 



45 



(1) AERODYNAMICS 



EFFECTS OF SWEEP AND TAPER RATIO ON THE 
LONGITUDINAL CHARACTERISTICS OF AN ASPECT 
RATIO 3 WING-BODY COMBINATION AT MACH 
NUMBERS FROM 0.6 TO 1.4. Earl D. Knechtel and 
James L. Summers. March i955. 36p. diagrs., 
photo. (NACA RM A55A03) 



TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF TAPER RATIO AND BODY IN- 
DENTATION ON THE AERODYNAMIC LOADING 
CHARACTERISTICS OF A 45° SWEPTBACK WING 
IN THE PRESENCE OF A BODY. James B. Delano 
and John P. Mugler, Jr. April 1955. 53p. diagrs., 
photos., tab. (NACA RM L54L28) 



COLLECTION AND SUMMARY OF FLAP-TYPE- 
AILERON ROLLING-EFFECTIVENESS DATA AT 
ZERO UFT AS DETERMINED BY ROCKET-. 
POWERED MODEL TESTS AT MACH NUMBERS 
BETWEEN 0.6 AND 1.6. H. Kurt Strass, Emily W. 
Stephens, E. M. Fields, and Eugene D. Schult. 
September 1955. 95p. diagrs., photos., tabs. 
(NACA RM L55F14) 



INVESTIGATION AT HIGH SUBSONIC SPEEDS OF 
THE STATIC LONGITUDINAL STABILITY CHARAC- 
TERISTICS OF A MODEL HAVING CROPPED-DELTA 
AND UNSWEPT WING PLAN FORMS AND SEVERAL 
TAIL CONFIGURATIONS . Albert G. Few, Jr. 
November 1955. 107p. diagrs., photo., tab. 
(NACA RM L 55123a) 



STATIC STABILITY CHARACTERISTICS OF A 
CAMBERED-DELTA-WTNG MODEL AT HIGH 
SUBSONIC SPEEDS. William C. Moseley, Jr. 
October 1956. 35p. diagrs., photos. 
(NACA RM L56H13) 



COMBINED EFFECTS OF WING TAPER RATIO AND 
LOW HORIZONTAL -TAIL POSITION ON LONGITU- 
DINAL STABILITY OF A 45° SWEPTBACK WING- 
BODY COMBINATION AT TRANSONIC SPEEDS. 
Stanley H. Spooner. October 1956. 28p. diagrs., 
tab. (NACA RM L56H24) 



THE USE OF PURE TWIST FOR DRAG REDUCTION 
ON ARROW WINGS WITH SUBSONIC LEADING 
EDGES. Frederick C. Grant. August 1957. 28p. 
diagrs., tabs. (NACA TN 4104) 



WIND-TUNNEL INVESTIGATION OF THE STATIC 
LATERAL STABILITY CHARACTERISTICS OF 
WING-FUSELAGE COMBINATIONS AT HIGH SUB- 
SONIC SPEEDS. TAPER-RATIO SERIES. James 
W. Wiggins and Paul G. Fournier. October 1957. 
25p. diagrs., photos. (NACA TN 4174. Supersedes 
RM L53B25a) 



GENERAL SOLUTIONS FOR FLOW PAST SLENDER 
CAMBERED WINGS WITH SWEPT TRAILING EDGES 
AND CALCULATION OF ADDITIONAL LOADING 
DUE TO CONTROL SURFACES. E. B. Klunker 
and Keith C. Harder. May 1958. 55p. diagrs. 
(NACA TN 4242) 



(1.2.2.2.5) 
Inlets and Exits 



THE EFFECT OF INLET INSTALLATION ON THE 
ZERO-LIFT DRAG OF A 60° DELTA-WING-BODY 
CONFIGURATION FROM FLIGHT TESTS AT MACH 
NUMBERS FROM 0.8 TO 1.86. Charles F. Merlet. 
December 1955. 29p. diagrs., photos., tabs. 
(NACA RM L55I09) 



(1.2.2.2.6) 
Surface Conditions 



AERODYNAMIC CHARACTERISTICS EXTENDED TO 
HIGH ANGLES OF ATTACK AT TRANSONIC SPEEDS 
OF A SMALL-SCALE 0° SWEEP WING, 45<> SWEPT- 
BACK WING, AND 60° DELTA WING. Harleth G. 
Wiley. November 1952. 26p. diagrs. 
(NACA RM L52I30) 



EFFECTS OF INCREASING REYNOLDS NUMBER 
FROM 2 x 106 TO 6 x 106 ON THE AERODYNAMIC 
CHARACTERISTICS AT TRANSONIC SPEEDS OF A 
450 SWEPT WING WITH 6» LEADING- EDGE DROOP. 
James W. SchmeeraudJ. Lawrence Cooper. 
Fehruary 1955. 22o. diaers.. Dhoto. 
(NACA RM L54L10)' 



COMPRESSIBILITY EFFECTS ON A HOVERING 
HELICOPTER ROTOR HAVING AN NACA 0018 ROOT 
AIRFOIL TAPERING TO AN NACA 0012 TIP AIR- 
FOIL. Robert D. Powell, Jr. September 1957. 
25p. diagrs. (NACA RM L57F26) 



EFFECTS OF COMPRESSIBILITY ON ROTOR HOV- 
ERING PERFORMANCE AND SYNTHESIZED BLADE- 
SECTION CHARACTERISTICS DERIVED FROM 
MEASURED ROTOR PERFORMANCE OF BLADES 
HAVING NACA 0015 AIRFOIL TD? SECTIONS. 
James P. Shivers and Paul J. Carpenter. September 
1958. 28p. diagrs. (NACA TN 4356) 



(1.2.2.2.7) 
Dihedral 



THE ROLLING MOMENT DUE TO SIDESLD? OF 
SWEPT WINGS AT SUBSONIC AND TRANSONIC 
SPEEDS. Edward C. Polhamus and William C . 
Sleeman, Jr. March 1955. 81p. diagrs., photos., 
tabs. (NACA RM L54L01) 



EXPLORATORY INVESTIGATION OF THE LOW- 
SPEED STATIC STABILITY OF A CONFIGURATION 
EMPLOYING THREE IDENTICAL TRIANGULAR 
WING PANELS AND A BODY OF EQUAL LENGTH. 
Noel K. Delany. April 1955. 25p. diagrs., photos. 
(NACA RM A55C28) 



COMPARISON OF THE STATIC STABILITY OF A 
68.7° DELTA-WING MODEL WITH DIHEDRAL AND 
A TWISTED AND CAMBERED WING MODEL OF THE 
SAME PLAN FORM. John W. Paulson. April 1955. 
18p. diagrs., tab. (NACA RM L55B11) 



46 



(1) AERODYNAMICS 



ADDITIONAL MEASUREMENTS OF THE LOW- 
SPEED STATIC STABILITY OF A CONFIGURATION 
EMPLOYING THREE TRIANGULAR WING PANELS 
AND A BODY OF EQUAL LENGTH. Noel K. Delany. 
July 1955. 31p. diagrs. (NACA RM A55F02a) 



LOW-SPEED INVESTIGATION OF THE EFFECTS 
OF WING DIHEDRAL ANGLE AND FIN LENGTH ON 
THE STATIC STABILITY CHARACTERISTICS OF A 
MODEL HAVING AN 82° DELTA WING. Kenneth P. 
Spreemann. April 1956. 30p. diagrs. 
(NACA RM L55L30a) 



STATIC STABILITY CHARACTERISTICS OF A 
CAMBERED-DELTA-WING MODEL AT HIGH 
SUBSONIC SPEEDS. William C. Moseley, Jr. 
October 1956. 35p. diagrs., photos. 
(NACA RML56H13) 



(1.2.2.3) 
HIGH-LIFT DEVICES 



EFFECTS OF LEADING-EDGE SLATS ON THE 
AERODYNAMIC CHARACTERISTICS OF A 45° 
SWEPTBACK WING-FUSELAGE CONFIGURATION 
AT MACH NUMBERS OF 0.4 TO 1.03. Jack F. 
Runckel and Seymour Steinberg. August 19 co 50p. 
diagrs., photos. (NACA RM L53F23) 



TRANSONIC FLIGHT MEASUREMENT OF THE 
AERODYNAMIC LOAD ON THE EXTENDED SLAT 
OF THE DOUGLAS D-558-H RESEARCH AIRPLANE. 
James R. Peele. August 1953. 34p. diagrs., 
photos., tab. (NACA RM L53F29) 



LOW-SPEED STATIC STABILITY AND CONTROL 
CHARACTERISTICS OF A 1/4-SCALE MODEL OF 
THE BELL X-l AIRPLANE EQUIPPED WITH A 
4-PERCENT-THICK, ASPECT-RATIO-4, UNSWEPT 
WING. William C. Moseley, Jr., and Robert T. 
Taylor. November 1953. 53p. diagrs., photos., 
tab. (NACA RM L53H27) 



EFFECTS OF LEADING -EDGE CHORD EXTENSIONS 
AND AN ALL-MOVABLE HORIZONTAL TAIL ON 
THE AERODYNAMIC CHARACTERISTICS OF A 
WING-fiODY COMBINATION EMPLOYING A TRI- 
ANGU1AR WING OF ASPECT RATIO 3 MOUNTED IN 
A HIGH POSITION AT SUBSONIC AND SUPERSONIC 
SPEEDS. Bentcr. E. Wetzel and Frank A. PfyL 
January 1954. 35p. diagrs., photo., tabs. 
(NACARM A53Ji'ia) 



STABILITY AND CONTROL CHARACTERISTICS 
OBTAINED DURING DEMONSTRATION OF THE 
DOUGLAS X-3 RESEARCH AIRPLANE. Richard E. 
Day and Jack Fischel. July 1955. 51p. diagrs., 
phoios., tab. (NACA. RM H55E16) 



FULL-SCALE WIND-TUNNEL TESTS OF A 35° 
SWEPTBACK-WINC AIRPLANE WITH HIGH- 
VELOCITY BLOWING OVER THE TRAILING -EDGE 
FLAPS - LONGITUDINAL AND LATERAL STABIL- 
ITY AND CONTROL. William H. Tolhurst, Jr., 
and Mark W. Kelly. October 1956. 64p. diagrs., 
photo., tabs. (NACA RM A56E24) 



A SUMMARY AND ANALYSIS OF THE LOW -SPEED 
LONGITUDINAL CHARACTERISTICS OF SWEPT 
WINGS AT HIGH REYNOLDS NUMBER. G. Chester 
Furlong and James G. McHugh. 1957. iii, 149p. 
diagrs., tabs. (NACA Rept. 1339. Supersedes 
RM L52D16) 



ESTIMATION OF INCREMENTAL PITCHING MO- 
MENTS DUE TO TRAILING-EDGE FLAPS ON 
SWEPT AND TRIANGULAR WINGS . Harry A. 
James and Lynn W. Hunton. July 1957. 31p. 
diagrs., tab. (NACA TN 4040. Supersedes 



FLIGHT INVESTIGATION OF THE LOW-SPEED 
CHARACTERISTICS OF A 3&o SWEPT -WING AIR- 
PLANE EQUIPPED WITH AN AREA-SUCTION 
EJECTOR FLAP AND VARIOUS WING LEADING- 
EDGE DEVICES. Seth B. Anderson, Alan E. Fayo, 
Jr., and Robert C. lnnis. September 1957. 28p. 
diagrs., photos., tab. (NACA RM A57G10) 



WIND-TUNNEL INVESTIGATION OF EXTERNAL- 
FLOW JET-AUGMENTED DOUBLE SLOTTED 
FLAPS ON A RECTANGULAR WING AT AN ANGLE 
OF ATTACK OF 0° TO HIGH MOMENTUM COEFFI- 
CIENTS. Edwin E, Davenport. September 1957. 
31p. diagrs., tabs. (NACA TN 4079) 



WIND-TUNNEL INVESTIGATION AT LOW SPEEDS 
TO DETERMINE FLOW-FIELD CHARACTERISTICS 
AND GROUND INFLUENCE ON A MODEL WITH 
JET-AUGMENTED FLAPS- Raymond D. Vogler and 
Thomas R. Turner. September 1957. 4 8p. diagrs., 
photos. (NACA TN 4116) 



TRANSITION -FLIGHT INVESTIGATION OF A 
FOUR-ENGINE-TRANSPORT VERTICAL-TAKE- 
OFF AIRPLANE MODEL UTILIZING A LARGE 
FLAP AND EXTENSIBLE VANES FOR REDIRECT- 
ING THE PROPELLER SLD?STREAM. Louis V. 
Tosti. December 1957. 35p. diagrs., photos., 
tab., film suppl. available on request. 
(NACA TN 4131) 



INVESTIGATION OF THE EFFECTS OF PRO- 
PELLER DIAMETER ON THE ABILITY OF A 
FLAPPED WING, WITH AND WITHOUT 
BOUNDARY- LAYER CONTROL, TO DE.^LSOT 
PROPELLER SLIPSTREAM DOWNWARD rdl 
VERTICAL TAKE-OFF. Kenneth P. Spreeman 
December J 957. 47p. diagrs., photos. 
(NACATN 4181) 



LOW-SPEED BOUNDARY- LAYER-CONTROL 
mVESTIGATION ON A THIN RECTANGULAR SEMI^ 
SPAN WING WITH LEADRJG-EDGE AND TRAILING- 
EDGE FLAPS. Delwin R. Groom and Thorn:-. . R. 
Turner. January 1958. 213p. diagrs., tab:-. 
(NACA RM L57J15) 



WIND 


_TT 


■NNEL INVE3TI 


GA r 


roN of 


THE 


Q 


LONC 


i; 


ion 


j.\L STAPH. 


17 1 


AND TP 


IM C 


('■. 


TEUi: : 


Tl 




V A SWEI', 


~tv. 




. .l: ; 




TRAV 


T 


/■;' 


' tfODET. V 


•I 7 * 1 


f W= '■ f 


■ 'V; ? 




EXT* 




■■? 


* <_.■>* t.v:t 


■AJJ 


■ W * 


:-' J I 




Jo3i?< 


, i'. 




,iir\ **.:... , >' i 




'.■ . ' i.V 






diagr. 




IV 


;\.*:-? 











47 



( 1 ) AERODY NAMICS 



Effectiveness of boundary- layer con- 
trol, OBTAINED BY BLOWING OVER A PLAIN 
REAR FLAP IN COMBINATION WITH A FORWARD 
SLOTTED FLAP, IN DEFLECTING A SLIPSTREAM 
DOWNWARD FOR VERTICAL TAKE-OFF. 
Kenneth P. Spreemann. February 1958. 32p. 
diagrs., photo. (NACA TN 4200) 



LOW -SUBSONIC INVESTIGATION TO DETERMINE 
THE CHORDWISE PRESSURE DISTRIBUTION AND 
EFFECTIVENESS OF SPOILERS ON A THIN, LOW- 
ASPECT-RATIO, UNSWEPT, UNTAPERED, SEMI- 
SPAN WING AND ON THE WING WITH LEADING- 
AND TRAILING-EDGE FLAPS. Delwin R. Croom. 
April 1958. 133p. diagrs., tabs. 
(NACA RM L58B05) 



EXPLORATORY WIND-TUNNEL INVESTIGATION TO 
DETERMINE THE LIFT EFFECTS OF BLOWING 
OVER FLAPS FROM NACELLES MOUNTED ABOVE 
THE WING. John M. Riebe and Edwin E. Davenport. 
June 1958. 19p. diagrs., tab. (NACA TN 4298) 



WIND-TUNNEL INVESTIGATION AT LOW SPEEDS 
OF FLIGHT CHARACTERISTICS OF A SWEPTBACK- 
WTNG JET-TRANSPORT AIRPLANE MODEL 
EQUIPPED WTTH AN EXTERNAL-FLOW JET- 
AUGMENTED SLOTTED I LAP. Joseph L. Johnson, 
Jr. July 1958. 32p. diagrs., photos., tab., film 
suppl. available on request. (NACA TN 4255) 



EFFECTS OF PROPELLER POSITION AND OVER- 
LAP ON THE SLIPSTREAM DEFLECTION CHAR- 
ACTERISTICS OF A WING-PROPELLER CONFIG- 
URATION EQUIPPED WITH A SLIDING AND 
FOWLER FLAP. William C. Hayes, Jr., Richard E. 
Kuhn, and Irving R. Sherman. September 1958. 
81p. diagrs., photos. (NACA TN 4404) 



(1.2.2.3. 1) 

Trailing-Edge Flaps 



WIND-TUNNEL TESTS OF A 0.16-SCALE MODEL 
OF THE X-3 AIRPLANE AT HIGH SUBSONIC 
SPEEDS. STABILITY AND CONTROL CHARACTER- 
ISTICS. William T. Hamilton and Joseph W. Cleary. 
April 21, 1950. 129p. diagrs., photos., tabs. 
(NACA RM A50A03) 



WIND-TUNNEL TESTS OF A 0.16-SCALE MODEL 
OF THE X-3 AIRPLANE AT HIGH SUBSONIC SPEEDS. 
- ADDITIONAL STABILITY AND CONTROL CHAR- 
ACTERISTICS AND THE AERODYNAMIC EFFECTS 
OF EXTERNAL STORES AND RAM JETS. Joseph W. 
Cleary and Jack A. Mellenthin. June 13, 1950. 86p. 
diagrs., photos., tabs. (NACA RM A50C30) 



AN INVESTIGATION OF A 0.16-SCALE MODEL OF 
THE DOUGLAS X-3 AIRPLANE TO DETERMINE 
MEANS OF IMPROVING THE LOW -SPEED LONGI- 
TUDINAL STABILITY AND CONTROL CHARACTER- 
ISTICS. John W. McKee and John M. Riebe. 
November 1952. 90p. diagrs., photos., tabs. 
(NACA RM L52H01) 



LOW-SPEED STATIC LONGITUDINAL AND LAT- 
ERAL STABILITY CHARACTERISTICS OF A MODEL 
WITH LEADING-EDGE CHORD-EXTENSIONS INCOR- 
PORATED ON A.40O SWFPTBACK CIRCULAR-ARC 
WING OF ASPECT RATIO 4 AND TAPER RATIO 0.50. 
Kenneth W. Goodson and Albert G. Few, Jr. 
November 1952. 46p. diagrs., photos., tab. 
(NACA RM L52I18} 



AERODYNAMIC CHARACTERISTICS OF A FULL- 
SPAN TRAILING-EDGE CONTROL ON A 60° DELTA 
WING WITH AND WITHOUT A SPOILER AT MACH 
NUMBER 1.61. Douglas R. Lord and K. R. 
Czarneckl. March 1954. 49p. diagrs., photos., 
tab. (NACARM L53L17) 



LOW-SPEED CHORDWISE PRESSURE DISTRIBU- 
TIONS NEAR THE MIDSPAN STATION OF THE 
SLOTTED FLAP AND AILERON OF A 1/4-SCALE 
MODEL OF THE BELL X-l AIRPLANE WITH A 
4 -PERCENT -THICK, ASPECT -RATIO-4, UNSWEPT 
WING. William C. Moseley, Jr., and Robert T. 
Taylor. March 1954. 59p. diagrs., photos., tabs. 
(NACA RM L53L18) 



AERODYNAMIC CHARACTERISTICS OF SEVERAL 
TIP CONTROLS ON A 60° DELTA WING AT A MACH 
NUMBEROF 1.61. Douglas R. LordandK. R. 
Czarnecki. August 1954. 44p. diagrs., photos., 
tabs. (NACA RM L54E25) 



EFFECTS OF OVERHANG BALANCE ON THE 
HINGE-MOMENT AND EFFECTIVENESS CHARAC- 
TERISTICS OF AN UNSWEPT TRAILING-EDGE 
CONTROL ON A 60° DELTA WING AT TRANSONIC 
AND SUPERSONIC SPEEDS. Lawrence D. Guy. 
September 1954. 48p. diagrs., photo. 
(NACA RM L54G12a) 



EFFECTS OF A DETACHED TAB ON THE HINGE- 
MOMENT AND EFFECTIVENESS CHARACTER- 
ISTICS OF AN UNSWEPT TRAILING-EDGE CON- 
TROL ON A 60° DELTA WING AT MACH NUMBERS 
FROM 0.75 TO 1.96. Odell A. Morris and 
Gertrude C, Westrick. April 1955. 36p. diagrs., 
photo. (NACA RM L55B15) 



EFFECT OF SEVERAL WING MODIFICATIONS ON 
THE LOW-SPEED STALLING CHARACTERISTICS OF 

THE DOUGLAS D-558-H RESEARCH AIRPLANE. 
Jack Fischel and Donald Reisert. July 1955. 62p. 
diagrs., photos., tabs. (NACA RM H55E31a) 



A HORIZONTAL -TAIL ARRANGEMENT FOR 
COUNTERACTING STATIC LONGITUDINAL 
INSTABILITY OF SWEPT BACK WINGS. George G. 
Edwards and Howard F. Savage. May 1956. 51p. 
diagrs., photos., tab. {NACA RM A56D06) 



INVESTIGATION OF THE USE OF AREA SUCTION 
TO INCREASE THE EFFECTIVENESS OF 
TRAILING-EDGE FLAPS OF VARIOUS SPANS ON 
A WING OF 45° SWEEPBACK AND ASPECT RATIO 
6. RoyN. Griffin, Jr., and David H. Hickey. 
June 1956. 64p. diagrs., photo., tabs. 
(NACA RM A56B27) 



48 



(1) AERODYNAMICS 



THE USE OF AREA SUCTION FOR THE PURPOSE 
OF IMPROVING THE LONGITUDINAL CHARACTER- 
ISTICS OF A THIN UNSWEPT-W1NG MODEL 
EQUIPPED WITH LEADING- AND TRA1LING-EDGE 
FLAPS. David G. Koenig. July 1956. 52p. 
diagrs., photo., tabs. (NACA RM A56D23) 



LOW-SPEED WIND-TUNNEL RESULTS FOR A THIN 
ASPECT-RATIO-1.85 POINTED-WING-FUSELAGE 
MODEL WITH DOUBLE SLOTTED FLAPS. Albert 
E. Brown. July 1956. 31p. diagrs., tabs. 
(NACA RM L56D03) 



BLOWING OVER THE FLAPS AND WING LEADING 
EDGE OF A THIN 49° SWEPT WING-BODY-TAIL 
CONFIGURATION IN COMBINATION WITH LEADING- 
EDGE DEVICES. H. Clyde McLemore and Marvin P. 
Fink. July 1956. 57p. diagrs., photo. 
(NACA RM L56E16) 



HINGE MOMENT AND EFFECTIVENESS OF AN 
UNSWEPT CONSTANT -CHORD CONTROL AND AN 
OVERHANG-BALANCED, SWEPT HINGE -LINE 
CONTROL ON AN 80° SWEPT POINTED WING AT 
MACH NUMBERS FROM 0.75 TO 1.96. Lawrence D. 
Guy. August 1956. 39p. diagrs., photo. 
(NACA RM L56F11) 



APPLICATION OF AREA SUCTION TO LEADING- 
EDGE AND TRAILING-EDGE FLAPS ON A 440 
SWEPT-WING MODEL. Curt A. Holzhauser, Robert 
K. Martin, and V. Robert Page. September 1956. 
66p. diagrs., photos., tabs. (NACA RM A56F01) 



EFFECT OF A FUSELAGE ON THE LOW-SPEED 
LONGITUDINAL AERODYNAMIC CHARACTERISTICS 
OF A 45° SWEPTBACK WING WITH DOUBLE 
SLOTTED FLAPS. Rodger L. Naeseth. September 
1956. 31p. diagrs., tabs. (NACA RM L56G02) 



WIND-TUNNEL TESTS OF BLOWING BOUNDARY- 
LAYER CONTROL WITH JET PRESSURE RATIOS 
UP TO 10 ON THE TRAILING-EDGE FLAPS OF A 
35° SWEPTBACK WING AIRPLANE. Mark W. Kelly 
and Jeffrey H. Tucker. October 1956. 24p. diagrs., 
photo., tab, (NACA RM A56G19) 



A LOW -SPEED INVESTIGATION OF A HIGH-LIFT 
LATERAL-CONTROL DEVICE CONSISTPNG OF A 
SPOILER-SLOT-DEFLECTOR AND A TRAILING- 
EDGE FLAP ON A TAPERED 45° SWEPTBACK 
WING. Alexander D. Hammond and Jarrett K. 
Huffman. October 1956. 21p. diagrs. 
(NACA RM L56H31) 



LARGE-SCALE WIND-TUNNEL TESTS OF AN AIR- 
PLANE MODEL WITH A 450 SWEPTBACK WING OF 
ASPECT RATIO 2.8 WITH AREA SUCTION APPLIED 
TO TRAILING-EDGE FLAPS AND WITH SEVERAL 
WING LEADING-EDGE MODIFICATIONS. David G 
Koenig and Kiyoshi Aoyagi. November 1956. 66p. 
diagrs., photo., tabs. (NACA RM A56H08) 



LOW -SPEED PRESSURE-DISTRIBUTION INVESTI- 
GATION OF A THIN-DELTA-WING-FUSELAGE 
MODEL WITH DOUBLE SLOTTED FLAP, EX- 
TENDED DOUBLE SLOTTED FLAP, AND CANARD. 
Delwin R. Croom and Jarrett K. Huffman. November 
1956. 104p. diagrs., tabs. (NACA RM L56I11) 



HIGH-PRESSURE BLOWING OVER FLAP AND WING 
LEADING EDGE OF A THIN LARGE-SCALE 49" 
SWEPT WING-BODY -TAIL CONFIGURATION IN 
COMBINATION WITH A DROOPED NOSE AND A 
NOSE WITH A RADIUS INCREASE. Marvin P. Fink 
andH. Clyde McLemore. May 1957. 40p. diagrs., 
photo. (NACA RM L57D23) 



AIR LOAD DISTRIBUTIONS ON A FLAPPED WING 

RESULTING FROM LEADING-EDGE AND TRAILING- 
EDGE BLOWING. H. Clyde McLemore. June 1957. 
9p. diagrs. (NACA RM L57D23b) 



ESTIMATION OF INCREMENTAL PITCHING MO- 
MENTS DUE TO TRAILING-EDGE FLAPS ON 
SWEPT AND TRIANGULAR WINGS. Harry A. 
James and Lynn W. Hunton. July 1957. 31p. 
diagrs., tab. (NACA TN 4040. Supersedes 
RM A55D07) 



THE SUBSONIC STATIC AERODYNAMIC CHARAC- 
TERISTICS OF AN AIRPLANE MODEL HAVING A 
TRIANGULAR WING OF ASPECT RATIO 3. 
IE - EFFECTS OF TRAILING-EDGE FLAPS. Bruce 
E. TinlingandA. V. Karpen. July 1957. 37p. 
diagrs., photos., tabs. (NACA TN 4043. Super- 
sedes RM A54L07) 



GROUND EFFECTS ON THE LONGITUDINAL CHAR- 
ACTERISTICS OF TWO MODELS WITH WINGS 
HAVING LOW ASPECT RATIO AND POINTED TIPS. 
Donald A. Buell and Bruce E. Tinling. July 1957. 
48p. diagrs., photos., tabs. (NACA TN 4044. 
Supersedes RM A55E04) 



WIND-TUNNEL INVESTIGATION AT LOW SPEEDS 
TO DETERMINE FLOW-FIELD CHARACTERISTICS 
AND GROUND INFLUENCE ON A MODEL WITH 
JET-AUGMENTED FLAPS. Raymond D. Vogler and 
Thomas R. Turner. September 1957. 48p. diagrs., 
photos. (NACATN 4116) 



WIND-TUNNEL INVESTIGATION OF EFFECTS OF 
GROUND PROXIMITY AND OF SPLIT FLAPS ON 
THE LATERAL STABILITY DERIVATIVES OF A 60° 
DELTA -WING MODEL OSCILLATING IN YAW. 
Byron M. Jaquet. September 1957. 32p. diagrs. 
photos., tab. (NACA TN 4119) 



THE USE OF A LEADING-EDGE AREA-SUCTION 
FLAP AND LEADING-EDGE MODIFICATIONS TO 
IMPROVE THE HIGH-LIFT CHARACTERISTICS OF 
AN AIRPLANE MODEL WITH A WING OF 450 
SWEEP AND ASPECT RATIO 2.8. David G. Koenig 
and Kiyoshi Aoyagi. November 1957. 46p. diagrs., 
photo., tabs. (NACA RM A57H21) 



WIND-TUNNEL INVESTIGATION OF THE USE OF 
LEADING-EDGE AND TRAILING-EDGE AREA- 
SUCTION FLAPS ON A 13-PERCENT-THICK 
STRAIGHT WING AND FUSELAGE MODEL. Curt A. 
Holzhauser. January 1958. 26p. diagrs., photo., 
tabs. (NACA RM A57K01) 



EXPERIMENTAL INVESTIGATION OF THE 
LATERAL TRIM OF A WING-PROPELLER COM- 
BINATION AT ANGLES OF ATTACK UP TO 90° 
WITH ALL PROPELLERS TURNING IN THE SAME 
DIRECTION. William A. Newsom, Jr. January 
1958. 27p. diagrs. (NACA TN 4190) 



49 



(1) AERODYNAMICS 



SURFACE PRFSSURE DISTRIBUTIONS ON A LARGE- 
SCALE 490 SWEPTBACK WING-BODY-TAIL CON- 
FIGURATION WITH BLOWING APPLIED OVER THE 
FLAPS AND WING LEADING EDGE. H. Clyde 
McLemore and Marvin P. Fink. February 1958. 
129p. diagrs., photo., tabs. (NACA RM L57K25) 



GENERAL SOLUTIONS FOR FLOW FAST SLENDER 
CAMBERED WINGS WITH SWEPT TRAILING EDGES 
AND CALCULATION OF ADDITIONAL LOADING 
DUE TO CONTROL SURFACES. E. B. Klunker 
and Keith C. Harder. May 1958. 55p. diagrs. 
(NACA TN 4242) 



FULL-SCALE WIND-TUNNEL TESTS OF A 35° 
SWEPTBACK-WING AIRPLANE WITH BLOWING 
FROM THE SHROUD AHEAD OF THE TRAILING- 
EDGE FLAPS. William H. Tolhurst, Jr. July 
1958. 40p. diagrs., photos., tabs. (NACA TN 4283) 



EXPLORATORY WIND-TUNNEL INVESTIGATION 
AT HIGH SUBSONIC AND TRANSONIC SPEEDS OF 
JET FLAPS ON UNSWEPT RECTANGULAR WINGS. 
Vernard E. Lockwood and Raymond D. Vogler. 
August 1958. 37p. diagrs. (NACA TN 4353) 



.LARGE-SCALE WIND-TUNNEL TESTS OF A JET- 
TRANSPORT-TYPE MODEL WITH LEADING- AND 
TRAILING-EDGE HIGH-LIFT DEVICES. David H. 
Hickey and Kiyoshi Aoyagi. September 1958. 32p. 
diagrs., photo., tabs. (NACA RM A58H12) 



LARGE-SCALE WIND-TUNNEL TESTS OF AN AIR- 
PLANE MODEL WITH AN UNSWEPT, ASPECT- 
RATIO- 10 WING, TWO PROPELLERS, AND AREA- 
SUCTION FLAPS. James A. Weiberg, Roy N. 
Griffin, Jr., and George L. Florman. September 
1958. 76p. diagrs., photos., tab. (NACA TN 4365) 



(1.2.2.3.2) 
Slots and Slats 



AN INVESTIGATION OF A 0.16-SCALE MODEL OF 
THE DOUGLAS X-3 AIRPLANE TO DETERMINE 
MEANS OF IMPROVING THE LOW-SPEED LONGI- 
TUDINAL STABILITY AND CONTROL CHARACTER- 
ISTICS. John W. McKee and John M. Riebe. 
November 1952. 90p. diagrs., photos., tabs. 
(NACA RM L52H01) 



EFFECTS OF LEADING-EDGE SLATS ON THE 
AERODYNAMIC CHARACTERISTICS OF A 45° 
SWEPTBACK WING -FUSELAGE CONFIGURATION 
AT MACH NUMBERS OF 0.4 TO 1.03. Jack F. 
Runckel and Seymour Steinberg. August 1953. 50p. 
diagrs., photos. (NACA RM L53F23) 



TRANSONIC FLIGHT MEASUREMENT OF THE 
AERODYNAMIC LOAD ON THE EXTENDED SLAT 
OF THE DOUGLAS D-558-II RESEARCH AIRPLANE. 
James R. Peele. August 1953. 34p. diagrs., 
photos., tab. (NACA RM L53F29) 



EFFECT OF WING SLATS AND INBOARD WING 
FENCES ON THE LONGITUDINAL STABILITY 
CHARACTERISTICS OF THE DOUGLAS D-558-II 
RESEARCH AIRPLANE IN ACCELERATED MANEU- 
VERS AT SUBSONIC AND TRANSONIC SPEEDS. 
Jack Fischel. February 1954. 125p. diagrs., 
photos., tabs. (NACA RM L53L16) 



EFFECT OF SEVERAL WING MODIFICATIONS ON 
THE LOW-SPEED STALLING CHARACTERISTICS OF 
THE DOUGLAS D-556-H RESEARCH AIRPLANE. 
Jack Fischel and Donald Reisert. July 1955. 62p. 
diagrs., photos., tabs. (NACA RM H55E31a) 



EFFECT OF SEVERAL WING MODIFICATIONS ON 
THE SUBSONIC AND TRANSONIC LONGITUDINAL 
HANDLING QUALITIES OF THE DOUGLAS D-558-II 
RESEARCH AIRPLANE. Jack Fischel and Donald 
Reisert. June 1956. 57p. diagrs., photos., tabs. 
(NACA RM H56C30) 



BLOWING OVER THE FLAPS AND WING LEADING 
EDGE OF A THIN 49° SWEPT WING- BODY -TAIL 
CONFIGURATION IN COMBINATION WITH LEADING- 
EDGE DEVICES. H. Clyde McLemore and Marvin P. 
Fink. July 1956. 57p. diagrs., photo. 
(NACA RM L56E16) 



HIGH-PRESSURE BLOWING OVER FLAP AND WING 
LEADING EDGE OF A THIN LARGE-SCALE 49° 
SWEPT WING-BODY -TAIL CONFIGURATION IN 
COMBINATION WITH A DROOPED NOSE AND A 
NOSE WITH A RADIUS INCREASE. Marvin P. Fink 
andH. Clyde McLemore. May 1957. 40p. diagrs., 
photo. (NACA RM L57D23) 



SURFACE PRESSURE DISTRIBUTIONS ON A LARGE- 
SCALE 490 SWEPTBACK WING-BODY -TAIL CON- 
FIGURATION WITH BLOWING APPLIED OVER THE 
FLAPS AND WING LEADING EDGE. H. Clyde 
McLemore and Marvin P. Fink. February 1958. 
129p. diagrs., photo., tabs. (NACA RM L57K25) 



LARGE-SCALE WIND-TUNNEL TESTS OF A JET- 
TRANSPORT -TYPE MODEL WITH LEADING- AND 
TRAILING-EDGE HIGH-LIFT DEVICES. David H. 
Hickey and Kiyoshi Aoyagi. September 1958. 32p. 
diagrs., photo., tabs. (NACA RM A58H12) 



(1.2.2.3.3) 
Leading-Edge Flaps 



WIND-TUNNEL TESTS OF A 0.16-SCALE MODEL 
OF THE X-3 AIRPLANE AT HIGH SUBSONIC 
SPEEDS. STABILITY AND CONTROL CHARACTER- 
ISTICS. William T. Hamilton and Joseph W. Cleary. 
April 21, 1950. 129p. diagrs., photos., tabs. 
(NACA RM A50A03) 



WIND-TUNNEL TESTS OF A 0.16-SCALE MODEL 
OF THE X-3 AIRPLANE AT HIGH SUBSONIC SPEEDS. 
- ADDITIONAL STABILITY AND CONTROL CHAR- 
ACTERISTICS AND THE AERODYNAMIC EFFECTS 
OF EXTERNAL STORES AND RAM JETS. Joseph W. 
Cleary and Jack A. Mellenthin. June 13, 1950. 86p. 
diagrs., photos., tabs. (NACA RM A50C30) 



WIND-TUNNEL TESTS OF A 0.16-SCALE MODEL 
OF THE X-3 AIRPLANE AT HIGH SUBSONIC SPEEDS. 
- WING AND FUSELAGE PRESSURE DISTRIBUTION. 
Joseph W. Cleary and Jack A. Mellenthin. June 22. 
1950. 6lp. diagrs., photos. (NACA RM A50DO7) 



50 



(1) AERODYNAMICS 



AN INVESTIGATION OF A 0.16 -SCALE MODEL OF 
THE DOUGLAS X-3 AIRPLANE TO DETERMINE 
MEANS OF IMPROVING THE LOW -SPEED LONGI- 
TUDINAL STABILITY AND CONTROL CHARACTER- 
ISTICS. John W. McKee and John M. Riebe. 
November 1952. 90p. diagrs., photos., tabs. 
(NACA RM L52H01) 



LOW-SPEED STATIC LONGITUDINAL AND LAT- 
ERAL STABILITY CHARACTERISTICS OF A MODEL 
WITH LEADING- EDGE CHORD- EXTENSIONS INCOR- 
PORATED ON A 40° SWEPTBACK CIRCULAR-ARC 
WING OF ASPECT RATIO 4 AND TAPER RATIO 0.50. 
Kenneth W. Goodson and Albert G. Few, Jr. 
November 1952. 46p. diagrs., photos., tab. 
(NACA RM L52I18) 



FREE-SPINNING-TUNNEL INVESTIGATION TO DE- 
TERMINE THE EFFECT OF SPINS AND RECOVER- 
IES OF WING LEADING- EDGE CHORD-EXTENSIONS 
AND DROOPED LEADING-EDGE FLAPS ON SCALE 
MODELS OF TWO SWEPTBACK-WING FIGHTER 
AIRPLANES. Jack H. Wilson and Walter J. Klinar 
May 1953. 28p. photo., diagrs., tabs. 
(NACA RM L53C06) 



RELATIONSHIP OF FLOW OVER A 4fi° SWEPT- 
BACK WING WITH AND WITHOUT LEADING-EDGE 
CHORD-EXTENSIONS TO LONGITUDINAL STABIL- 
ITY CHARACTERISTICS AT MACH NUMBERS FROM 
0.60 TO 1.03. F E. West. Jr , and James H 
Henderson. October 1953 47p diagrs , photos. 
(NACA RM L53H18b) 



LONGITUDINAL CHARACTERISTICS OF WINGS. 

Thomas A. Toll. October 1953. 18p. diagrs. 
(NACA RM L53I21b) 



DRAG DUE TO LIFT AT MACH NUMBERS UP TO 2.0. 
Edward C. Polhamus. November 1953. 18p. diagrs. 
(NACA RM L53I22b) 



EFFECT OF A WING LEADING -EDGE FLAP AND 
CHORD-EXTENSION ON THE HIGH SUBSONIC 
CONTROL CHARACTERISTICS OF AN AILERON 
LOCATED AT TWO SPANWISE POSITIONS. Robert 
F. Thompson and Robert T- Taylor. May 1955. 
59p. diagrs., photo., tabs. (NACA RM L55B18a) 



A SYSTEMATIC STUDY OF THE EFFECTS OF 
LEADING-EDGE CHORD- EXTENSIONS ON THE 
LOW-SPEED LONGITUDINAL STABILITY CHARAC- 
TERISTICS OF THREE 45° SWEPTBACK WINGS. 
H. Neale Kelly. October 1955. 113p. diagrs., 
photo., tabs. (NACARM L55H19) 



THE EFFECT OF LEADING-EDGE DROOP UPON 
THE PRESSURE DISTRIBUTION AND AERODYNAM- 
IC LOADING CHARACTERISTICS OF A 45° SWEPT- 
BACK WING AT TRANSONIC SP EEDS - James W . 
Schmeer. November 1955. 42p. diagrs., photos. 
(NACA RM L55I16) 



THE USE OF AREA SUCTION FOR THE PURPOSE 
OF IMPROVING THE LONGITUDINAL CHARACTER- 
ISTICS OF A THIN UNSWEPT-WING MODEL 
EQUIPPED WITH LEADING- AND TRAILING-EDGE 
FLAPS. David G. Koenig. July 1956. 52p. 
diagrs., ohoto., tabs. (NACA RM A56D23) 



APPLICATION OF AREA SUCTION TO LEADING- 
EDGE AND TRAILING-EDGE FLAPS ON A 44° 
SWEPT-WING MODEL. Curt A. Holzhauser, Robert 
K. Martin, and V. Robert Page. September 1956. 
66p. diagrs., photos., tabs. (NACA RM A56F01) 



LARGE-SCALE WIND-TUNNEL TESTS OF AN AIR- 
PLANE MODEL WITH A 45<> SWEPTBACK WING OF 
ASPECT RATIO 2.8 WITH AREA SUCTION APPLIED 
TO TRAILING-EDGE FLAPS AND WITH SKVEKAL 
WING LEADING-EDGE MODIFICATIONS. David G 
Koenig and Kiyoshi Aoyagi. November 1956. tiOp. 
diagrs., photo., tabs. (NACARM A56H08) 



WING LOADS AND LOAD DISTRIBUTIONS THROUGH- 
OUT THE LIFT RANGE OF THE DOUGLAS X-3 
RESEARCH AIRPLANE AT TRANSONIC SPEEDS. 
Earl R. Keener and Gareth H. Jordan. November 
1956. 191p. diagrs., photo., tabs. 
(NACA RM H56G13) 



THE USE OF A LEADING-EDGE AREA-SUCTION 
FLAP AND LEADING-EDGE MODIFICATIONS TO 
IMPROVE THE HIGH-LIFT CHARACTERISTICS OF 
AN AIRPLANE MODEL WITH A WING OF 45° 
SWEEP AND ASPECT RATIO 2.8. David G. Koenig 
and Kiyoshi Aoyagi. November 1957. 46p. diagrs., 
photo., tabs. (NACA RM A57H21) 



FLIGHT DATA PERTINENT TO BUFFETING AND 
MAXIMUM NORMAL-FORCE COEFFICIENT OF THE 
DOUGLAS X-3 RESEARCH AIRPLANE. Thomas F. 
Baker, James A. Martin, and Betty J. Scott. 
November 1957. 41p. diagrs., photo., tabs. 
(NACA RM H57H09) 



WIND-TUNNEL INVESTIGATION OF THE USE OF 
LEADING-EDGE AND TRAILING-EDGE AREA- 
SUCTION FLAPS ON A 13-PERCENT-THICK 
STRAIGHT WING AND FUSELAGE MODEL. Curt A. 
Holzhauser. January 1958. 26p, diagrs., photo., 
tabs. (NACA RM A57K01) 



SURFACE PRESSURE DISTRIBUTIONS ON A LARGE- 
SCALE 490 SWEPTBACK WING- BODY -TAIL CON- 
FIGURATION WITH BLOWING APPLIED OVER THE 
FLAPS AND WING LEADING EDGE. H. Clyde 
McLemore and Marvin P. Fink. February 1958. 
129p. diagrs., photo., tabs. (NACARM L57K25) 



THE EFFECTS OF AN INVERSE -TAPER LEADING- 
EDGE FLAP ON THE AERODYNAMIC CHARACTER- 
ISTICS IN PITCH OF A WING-BODY COMBINATION 
HAVING AN ASPECT RATIO OF 3 AND 45° OF 
SWEEPBACK AT MACH NUMBERS TO 0.92. Fred A. 
Demele and K. Harmon Powell. August 1958. 57p. 
diagrs., photo., tabs. (NACA TN 4366) 



(1.2.2.4) 
CONTROLS 



HINGE-MOMENT CHARACTERISTICS FOR SEVER- 
AL TIP CONTROLS ON A 60° SWEPTBACK DELTA 
WING AT MACH NUMBER 1.61. K. R. Czamecki 
and Douglas R. Lord. January 1953. 31p. diagrs., 
photos. (NACA RM L52K28) 



51 



(1) AERODYNAMICS 



AN EXPERIMENTAL INVESTIGATION AT SUBSONIC 
AND SUPERSONIC SPEEDS OF THE TORSIONAL 
DAMPING CHARACTERISTICS OF A CONSTANT- 
CHORD CONTROL SURFACE OF AN ASPECT RATIO 
2 TRIANGULAR WING. David E. Reese, Jr. July 
1953. 32p. diagrs., photos., tab. 
(NACA RM A53D271 



CONTROL HINGE-MOMENT AND EFFECTIVENESS 
CHARACTERISTICS OF SEVERAL INTERCHANGE- 
ABLE TIP CONTROLS ON A 60° DELTA WING AT 
MACH NUMBERS OF 1.41, 1.62, AND 1.96. Odell 
A. Morris. November 1953. 33p. diagrs., photo., 
tab. (NACA RM L53j08a) 



AERODYNAMIC CHARACTERISTICS OF SEVERAL 
TIP CONTROLS ON A 60° DELTA WING AT A MACH 
NUMBER OF 1.61. Douglas R. Lord and K. R. 
Czarnecki. August 1954. 44p. diagrs., photos., 
tabs. (NACA RM L54E25) 



STABILITY AND CONTROL CHARACTERISTICS 
OBTAINED DURING DEMONSTRATION OF THE 
DOUGLAS X-3 RESEARCH AIRPLANE. Richard E. 
Day and Jack Fischel. July 1955. 51p. diagrs., 
photos., tab. (NACA RMH55E16) 



WING PRESSURE DISTRIBUTIONS OVER THE LIFT 
RANGE OF THE CONVAIR XF-92A DELTA-WING 
AIRPLANE AT SUBSONIC AND TRANSONIC 
SPEEDS. Earl R. Keener and Gareth H. Jordan. 
November 1955. 135p. diagrs., photos., tabs. 
(NACA RM H55G07) 



WIND-TUNNEL INVESTIGATION AT HIGH SUBSONIC 
SPEEDS OF JET, SPOILER, AND AILERON CON- 
TROLS ON A 1/16-SCALE MODEL OF THE DOUGLAS 
D-558-H RESEARCH AIRPLANE. Raymond D. 
Vogler. July 1956. 52p. diagrs., photo., tabs. 
(NACA RM L56E25) 



FLIGHT INVESTIGATION OF THE TRANSONIC 
LONGITUDINAL AND LATERAL HANDLING QUAL- 
ITIES OF THE DOUGLAS X-3 RESEARCH AIRPLANE. 
Jack Fischel, Euclid C. Ho lie man, and Robert A. 
T rem ant. December 1957. 61p. diagrs., photos., 
tab. (NACA RM H57I05) 



GENERAL SOLUTIONS FOR FLOW PAST SLENDER 
CAMBERED WINGS WITH SWEPT TRAILING EDGES 
AND CALCULATION OF ADDITIONAL LOADING 
DUE TO CONTROL SURFACES. E. B. Klunker 
and Keith C. Harder. May 1958. 55p. diagrs. 
(NACA TN 4242) 



(1.2.2.4. 1) 
Flap Type 



PRELIMINARY INVESTIGATION AT A MACH NUM- 
BER OF 1 .9 AND A REYNOLDS NUMBER OF 
2,200,000 OF THREE AILERONS APPLICABLE TO 
THE BELL XS-2 AmPLANE DESIGN. James C. 
Sivells and D. William Conner. May 25, 1948. 
lip. diagrs., tab. (NACA RM L8D02) 



AERODYNAMIC STUDY OF A WING-FUSELAGE 
COMBINATION EMPLOYING A WING SWEPT BACK 
63«. . EFFECTS AT SUBSONIC SPEEDS OF A 
CONSTANT-CHORD ELEVON ON A WING CAM- 
BERED AND TWISTED FOR A UNIFORM LOAD AT 
A LIFT COEFFICIENT OF 0.25. J. Lloyd Jones and 
Fred A. Demele. December 5, 1949. 44p. diagrs., 
photos., tab, (NACA RM A9I27* 



WIND-TUNNEL TESTS OF A 0.16-SCALE MODEL 
OF THE X-3 AIRPLANE AT HIGH SUBSONIC SPEEDS. 
- ADDITIONAL STABILITY AND CONTROL CHAR- 
ACTERISTICS AND THE AERODYNAMIC EFFECTS 
OF EXTERNAL STORES AND RAM JETS. Joseph W. 
Cleary and Jack A. MeUenthin. June 13, 1950. 86p. 
diagrs., photos., tabs. (NACA RM A50C30) 



INVESTIGATION OF THE AERODYNAMIC EFFECTS 
OF AN EXTERNAL STORE IN COMBINATION WITH 
60° DELTA AND LOW-ASPECT-RATIO TAPERED 
WINGS AT A MACH NUMBER OF 1.9. Ellery B. 
May, Jr. January 9, 1951. 46p. diagrs., photos. 
(NACA RM L50K03) 



AN INVESTIGATION AT MACH NUMBERS OF 1 .40 
AND 1.59 OF THE EFFECTS OF AILERON PROFILE 
ON THE AERODYNAMIC CHARACTERISTICS OF A 
COMPLETE MODEL OF A SUPERSONIC AIRCRAFT 
CONFIGURATION. M. Leroy Spearman and Robert 
A. Webster. January 15, 1951. 40p. diagrs., 
photos., tabs. (NACA RM L50J31) 



FREE-FLIGHT MEASUREMENTS AT MACH NUM- 
BERS FROM 0.7 TO 1.6 OF SOME EFFECTS OF 
AIRFOIL-THICKNESS DISTRIBUTION AND 
TRAILING-EDGE ANGLE ON AILERON ROLLING 
EFFECTIVENESS AND DRAG FOR WINGS WITH 0° 
AND 45° SWEEP BACK. E. M. Fields and H. Kurt 
Strass. October 1951. 63p. diagrs., photos., tab. 
(NACA RM L51G27) 



FLIGHT DETERMINATION OF THE DRAG AND 
LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A ROCKET -POWERED MODEL 
OF A 60<> DELTA-WING AIRPLANE FROM MACH 
NUMBERS OF 0.75 TO 1.70. Grady L. Mitcham, 
Norman L. Crablll, and Joseph E. Stevens. 
November 19 51 . 44p . diagrs . , photos . , tab . 
(NACA RM L51I04) 



SUMMARY OF SOME EFFECTIVE AERODYNAMIC 
TWISTING-MOMENT COEFFICIENTS OF VARIOUS 
WING -CONTROL CONFIGURATIONS AT MACH 
NUMBERS FROM 0.6 TO 1.7 AS DETERMINED 
FROM ROCKET-POWERED MODELS. H. Kurt 
Strass. January 1952. 22p. diagrs., photo., 
2 tabs. (NACA RM L51K20) 



LOAD DISTRIBUTIONS ASSOCIATED WITH CON- 
TROLS AT SUPERSONIC SPEEDS. K. R. Czarnecki 
and Douglas R. Lord. May 1953. 21p. ohoto., 
diagrs. (NACA RM L53D15a) 



LOADS DUE TO FLAPS AND SPOILERS ON SWEPT - 
BACK WINGS AT SUPERSONIC AND TRANSONIC 
SPEEDS. Alexander D. Hammond and F. E. West, 
Jr. June 1953. 17p. diagrs. {NACA RM L53D29a) 



52 



( 1 ) AERODYNAMICS 



AN EXPERIMENTAL INVESTIGATION AT SUBSONIC 
AND SUPERSONIC SPEEDS OF THE TORSIONAL 
DAMPING CHARACTERISTICS OF A CONSTANT- 
CHORD CONTROL SURFACE OF AN ASPECT RATIO 
2 TRIANGULAR WING. David E. Reese, Jr. July 
1953. 32p. diagrs., photos., tab. 
(NACA RM A53D27) 



SUBSONIC AND SUPERSONIC HINGE -MOMENT AND 
EFFECTIVENESS CHARACTERISTICS OF AN UN- 
BALANCED LATERAL CONTROL HAVING LOW 
THEORETICAL HINGE MOMENTS AT SUPERSONIC 
SPEEDS. Kennith L. Goln and William E. Palmer. 
October 1953. 55p. diagrs., photos. 
(NACA RM L53G31a) 



RECENT EXPERIENCES WITH FLUTTER FAILURE 
OF SWEPTBACK, TAPERED WINGS HAVING OUT- 
BOARD. PARTIAL-SPAN SPOILER CONTROLS. 
H. Kurt Strass and Edward T. Marley. October 
1953. 20p. diagis., photos., tabs 
(NACA RM L53H26) 



INVESTIGATION OF A TRAILING-EDGE PADDLE- 
CONTROL SURFACE ON A TRIANGULAR WING OF 
ASPECT RATIO 2 AT SUBSONIC AND SUPERSONIC 
SPEEDS. Louis H. Ball. February 1954. 18p. 
diagrs., tab. (NACA RM A53K20) 



AERODYNAMIC CHARACTERISTICS OF A FULL- 
SPAN TRAILING-EDGE CONTROL ON A 60° DELTA 
WING WITH AND WITHOUT A SPOILER AT MACH 
NUMBER 1.61. Douglas R. Lord and K. R- 
Czarneckl. March 1954. 49p. diagrs., photos., 
tab. (NACARML53L17) 



LOW-SPEED CHORDWISE PRESSURE DISTRIBU- 
TIONS NEAR THE MIDSPAN STATION OF THE 
SLOTTED FLAP AND AILERON OF A 1/4-SCALE 
MODEL OF THE BELL X-l AIRPLANE WITH A 
4-PERCENT-THICK, ASPECT -RATTO-4, UNSWEPT 
WING. William C. Moseley, Jr., and Robert T. 
Taylor. March 1954. 59p. diagrs., photos., tabs. 
(NACA RM L53L18) 



AERODYNAMIC CHARACTERISTICS OF SEVERAL 
TIP CONTROLS ON A 60° DELTA WING AT A MACH 
NUMBER OF 1.61. Douglas R. Lord and K. R. 
Czarnecki. August 1954. 44p. diagrs., photos., 
tabs. (NACA RM L54E25) 



EFFECTS OF OVERHANG BALANCE ON THE 
HINGE -MOMENT AND EFFECTWENESS CHARAC- 
TERISTICS OF AN UNSWEPT TRAILING-EDGE 
CONTROL ON A 60° DELTA WING AT TRANSONIC 
AND SUPERSONIC SPEEDS. Lawrence D. Guy. 
September 1954. 48p. diagrs., photo. 
(NACA RM L54G12a) 



SOME EFFECTS OF AILERON SPAN, AILERON 
CHORD, AND WING TWIST ON ROLLING EFFEC- 
TIVENESS AS DETERMINED BY ROCKET- 
POWERED MODEL TESTS AND THEORETICAL 
ESTIMATES. H. Kurt Strass and Warren A. Tucker. 
September 1954. 29p. diagrs., photos., tabs. 
(NACA RM L54G13) 



FREE -FLIGHT MEASUREMENTS OF THE ROLLING 
EFFECITVENESS AND OPERATING CHARACTER- 
ISTICS OF A BELLOWS-ACTUATED SPLIT-FLAP 
AILERON ON A 60° DELTA WING AT MACH NUM- 
BERS BETWEEN 0.8 AND 1.8. Eugene D. Schult. 
October 1954. 33p. diagrs., photos. 
(NACA RM L54H17) 



ROLLING PERFORMANCE OF THE REPUBLIC 
YF-84F AIRPLANE AS MEASURED IN FLIGHT. 
JohnB. McKay. January 1955. 24p. diagrs., 
photo., tab. (NACA RM H54G20a) 



FREE -FLIGHT INVESTIGATION TO DETERMINE 
SOME EFFECTS OF TAIL DAMPING AND WING- 
TAIL INTERFERENCE ON THE ROLLING EFFEC- 
TIVENESS OF INBOARD AND OUTBOARD AILERONS 
ON AN UNTAPERED SWEPTBACK WING . Roland D. 
English. March 1955. 18p. diagrs., photos. 
(NACA RM L54Ll7a) 



EFFECTS OF A DETACHED TAB ON THE HINGE - 
MOMENT AND EFFECTIVENESS CHARACTER- 
ISTICS OF AN UNSWEPT TRAILING-EDGE CON- 
TROL ON A 60° DELTA WING AT MACH NUMBERS 
FROM 0.75 TO 1.96. Odell A. Morris and 
Gertrude C. Westrick. April 1955. 36p. diagrs., 
photo. (NACA RM L55B15) 



EFFECT OF A WING LEADING-EDGE FLAP AND 
CHORD-EXTENSION ON THE HIGH SUBSONIC 
CONTROL CHARACTERISTICS OF AN AILERON 
LOCATED AT TWO SPANWISE POSITIONS. Robert 
F. Thompson and Robert T. Taylor. May 1955. 
59p. diagrs., photo., tabs. (NACA RM L55B 18a) 



COLLECTION AND SUMMARY OF FLAP-TYPE- 
AILERON ROLLING -EFFECTIVENESS DATA AT 
ZERO LIFT AS DETERMINED BY ROCKET- 
POWERED MODEL TESTS AT MACH NUMBERS 
BETWEEN 0.6 AND 1.6. H. Kurt Strass, Emily W. 
Stephens, E. M. Fields, and Eugene D. Schult. 
September 1955. 95p. diagrs., photos., tabs. 
(NACARM L55F14) 



SOME EFFECTS OF AILERONS ON THE VARIATION 
OF AERODYNAMIC CHARACTERISTICS WITH SIDE- 
SLIP AT LOW SPEED. Kenneth W- Goodson. 
March 1956. 40p. diagrs., tab. (NACA RM L55L20) 



AERODYNAMIC DAMPING AT MACH NUMBERS OF 
1.3 AND 1.6 OF A CONTROL SURFACE ON A TWO- 
DIMENSIONAL WING BY THE FREE -OSCILLATION 
METHOD. W. J. Tuovila and Robert W- Hess. 
May 1956. 21p. diagrs., tabs. (NACA RM L56A26a) 



INVESTIGATION OF THE USE OF AREA SUCTION 
TO INCREASE THE EFFECTIVENESS OF 
TRAILING-EDGE FLAPS OF VARIOUS SPANS ON 
A WING OF 45° SWEEPBACK AND ASPECT RATIO 
6. RoyN. Griffin, Jr., and David H. Hickey. 
June 1956. 64p. diagrs., photo., tabs. 
(NACA RM A56B27) 



THE VARIATION WITH WING ASPECT RATIO OF 
FLAP EFFECTIVENESS ON THTN RECTANGULAR 
WINGS AT TRANSONIC SPEEDS, John G. Lowry 
and Robert T. Taylor. August 1956. 60p. diagrs., 
tabs. (NACARML56E18) 



HINGE MOMENT AND EFFECTIVENESS OF AN 
UNSWEPT CONSTANT -CHORD CONTROL AND AN 
OVERHANG-BALANCED, SWEPT HINGE-LINE 
CONTROL ON AN 80° SWEPT POINTED WING AT 
MACH NUMBERS FROM 0.75 TO 1.96. Lawrence D. 
Guy. August 1956. 39p. diagrs., photo. 
(NACARM L56F11) 



53 



(1) AERODYNAMICS 



FULL-SCALE WIND-TUNNEL TESTS OF A 35° 
SWEPTBACK-WING AIRPLANE WITH HIGH- 
VELOCITY BLOWING OVER THE TRAILING-EDGE 
FLAPS - LONGITUDINAL AND LATERAL STABIL- 
ITY AND CONTROL. William H. Tolhurst, Jr., 
and Mark W. Kelly. October 1956. 64p. diagrs., 
photo., tabs. (NACA RM A56E24) 



THE EFFECT OF EXTERNAL STIFFENING RIBS ON 
THE ROLLING POWER OF AILERONS ON A SWEPT 
WING. Emily W. Stephens. October 1956. 15p, 
diagrs., photo., tab. (NACA RM L56D19) 



EXPERIMENTAL HINGE MOMENTS ON FREELY 
OSCILLATING FLAP-TYPE CONTROL SURFACES. 
C. William Martz. October 1956. 29p. diagrs., 
photos., tab. (NACA RM L56G20) 



GROUND EFFECTS ON THE LONGITUDINAL CHAR- 
ACTERISTICS OF TWO MODELS WITH WINGS 
HAVING LOW ASPECT RATIO AND POINTED TIPS. 
Donald A. Buell and Bruce E. Tin ling. July 1957. 
48p. diagrs., photos., tabs. (NACA TN 4044. 
Supersedes RM A55E04) 



WIND-TUNNEL INVESTIGATION OF EXTERNAL- 
FLOW JET-AUGMENTED DOUBLE SLOTTED 
FLAPS ON A RECTANGULAR WING AT AN ANGLE 
OF ATTACK OF 0° TO HIGH MOMENTUM COEFFI- 
CIENTS. Edwin E. Davenport. September 1957. 
31p. diagrs., tabs. (NACA TN 4079) 



LOW-SPEED BOUNDARY- LAYER-CONTROL 
INVESTIGATION ON A THIN RECTANGULAR SEMI- 
SPAN WING WITH LEADING-EDGE AND TRAILING- 
EDGE FLAPS. Delwin R, Croom and Thomas R. 
Turner. January 1958. 21 3p. diagrs., tabs. 
(NACA RM L57J15) 



WIND-TUNNEL INVESTIGATION OF THE STATIC 
LONGITUDINAL STABILITY AND TRIM CHARAC- 
TERISTICS OF A SWEPTBACK-WING JET- 
TRANSPORT MODEL EQUIPPED WITH AN 
EXTERNAL-FLOW JET-AUGMENTED FLAP. 
Joseph L Johnson, Jr. January 1958. 89p. 
diagrs., tab. (NACA TN 4177) 



EXPLORATORY WIND-TUNNEL INVESTIGATION TO 
DETERMINE THE LIFT EFFECTS OF BLOWING 
OVER FLAPS FROM NACELLES MOUNTED ABOVE 
THE WING. John M. Rlebe and Edwin E. Davenport. 
June 1958. 19p. diagrs., tab. (NACA TN 4298) 



SOME FACTORS AFFECTING THE VARIATION OF 
PITCHING MOMENT WITH SIDESLIP OF AIRCRAFT 
CONFIGURATIONS. Edward C. Polhamus. August 
1958. 35p. diagrs., photo. (NACA TN 4016. 
Supersedes RM L55E20b) 



(1,2.2.4.2) 

Spoilers 



SUMMARY OF SOME EFFECTIVE AERODYNAMIC 
TWISTING-MOMENT COEFFICIENTS OF VARIOUS 
WING-CONTROL CONFIGURATIONS AT MACH 
NUMBERS FROM 0.6 TO 1.7 AS DETERMINED 
FROM ROCKET-POWERED MODELS. H. Kurt 
Strass. January 1952. 22p, diagrs., photo., 
2 tabs. (NACA RM L51K20) 



FREE-FLIGHT MEASUREMENTS OF SOME EF- 
FECTS OF SPOILER SPAN AND PROJECTION AND 
WING FLEXIBILITY ON ROLLING EFFECTIVENESS 
AND DRAG OF PLAIN SPOILERS ON A TAPERED 
SWEPTBACK WING AT MACH NUMBERS BETWEEN 
0.6 AND 1.6. Eugene D. SchultandE. M. Fields. 
October 1952. 30p. diagrs., photo., tab. 
(NACA RM L52HG6a) 



LOAD DISTRIBUTIONS ASSOCIATED WITH CON- 
TROLS AT SUPERSONIC SPEEDS- K. R. Czarneckl 
and Douglas R. Lord. Mav 1953. 21p. photo., 
diagrs. (NACA RM L53D13a) 



LOADS DUE TO FLAPS AND SPOILERS ON SWEPT- 
BACK WINGS AT SUPERSONIC AND TRANSONIC 
SPEEDS. Alexander D. Hammond and F. E. West, 
Jr. June 1953. 17p. diagrs. (NACA RM L53D29a) 



INVESTIGATION OF SPOILER AILERONS WITH AND 
WITHOUT A GAP BEHIND THE SPOILER ON A 45° 
SWEPTBACK WING-FUSELAGE COMBINATION AT 
MACH NUMBERS FROM 0.60 TO 1.03. F. E. West, 
Jr., William Solomon, and Edward M. Brummal. . 
September 1953. 38p. diagrs. (NACA RM L53G07a) 



RECENT EXPERIENCES WITH FLUTTER FAILURE 
OF SWEPTBACK, TAPERED WINGS HAVING OUT- 
BOARD, PARTIAL-SPAN SPOILER CONTROLS. 
H. Kuril Strass and Edward T. Marley. October 
1953. 20p. diagrs., photos., tabs. 
(NACAlRM L53H26) 



DATA ON SPOILER-TYPE AILERONS. 
Lowry. October 1953. 27p. diagrs. 
(NACA RM L53I24a) 



John G. 



WIND-TUNNEL INVESTIGATIONS AT LOW AND 
TRANSONIC SPEEDS OF THE FEASIBILITY OF 
SELF -ACTUATING SPOILERS AS A LATERAL- 
CONTROL DEVICE FOR A MISSILE. Harleth G. 
Wiley and William C. Hayes, Jr. January 1954. 
24p. diagrs., tab. (NACA RM L53K27) 



AERODYNAMIC CHARACTERISTICS OF A FULL- 
SPAN TRAILING-EDGE CONTROL ON A 60° DELTA 
WING WITH AND WITHOUT A SPOILER AT MACH 
NUMBER 1.61. Douglas R. Lord and K. R. 
Czarneckl. March 1954. 49p. diagrs., photos., 
tab. (NACA RM L53L17) 



EFFECTS OF SPOILER AILERONS ON THE AERO- 
DYNAMIC LOAD DISTRIBUTION OVER A 45© 
SWEPTBACK WING AT MACH NUMBERS FROM 0.60 
TO 1.03. Joseph M. Hallissy, Jr., F. E. West, Jr., 
and George Liner. May 1954. 162p. diagrs., tabs. 
(NACA RML54C 17a) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR-ARC SECTIONS AND 40<> SWEEPBACK. 
STABILITY AND CONTROL CHARACTERISTICS AT 
A MACH NUMBER OF 1.61 OF THE COMPLETE 
CONFIGURATION EQUIPPED WITH SPOILERS. 
Clyde V. Hamilton and Cornelius Driver. September 
1954. 28p. diagrs. (NACA RM L54F15) 



54 



(1) AERODYNAMICS 



FREE -FLIGHT MEASUREMENTS OF THE ROLLING 
EFFECTIVENESS AND OPERATING CHARACTER- 
ISTICS OF A BELLOWS-ACTUATED SPLIT-FLAP 
AILERON ON A 60° DELTA WING AT MACH NUM- 
BERS BETWEEN 0.8 AND 1.8. Eugene D. Schult. 
October 1954. 33p. dtagrs., photos. 
(NACA RM L54H17) 



COMPARISON OF EFFECTS OF AILERONS AND 
COMBINATIONS OF SPOILER-SLOT-DEFLECTOR 
ARRANGEMENTS ON SPIN RECOVERY OF SWEPT- 
BACK-WING MODEL HAVING MASS DISTRIBUTED 
ALONG THE FUSELAGE. Frederick M. Healy and 
Walter J. Klinar. November 1954. 18p. diagrs., 
photo., tabs. (NACA RM L54I14) 



WIND-TUNNEL INVESTIGATION AT TRANSONIC 
SPEEDS OF A JET CONTROL ON AN 80° DELTA- 
WING MISSILE. Thomas R. Turner and Raymond D. 
Vogler. November 1955. 32p. diagrs. 
(NACA RM L55H22) 



LOW-SPEED PRESSURE -DISTRIBUTION INVESTI- 
GATION OF A SPOILER AND A SPOILER-SLOT- 
DEFLECTOR ON A 30° SWEPTBACK WING- 
FUSELAGE MODEL HAVING AN ASPECT RATIO 
OF 3, A TAPER RATIO OF 0.5, AND NACA 65A004 
AIRFOIL SECTION. Alexander D. Hammond. 
January 1956. 176p. diagrs., tabs. 
(NACA RM L55I29) 



WIND-TUNNEL INVESTIGATION AT TRANSONIC 
SPEEDS OF A JET CONTROL ON A 35° SWEPT 
WING. TRANSONIC-BUMP METHOD. Raymond D. 
Vogler and Thomas R. Turner. February 1956. 
17p. diagrs. (NACA RM L55K09) 



AERODYNAMIC LOADINGS ASSOCIATED WITH 
SWEPT AND UNSWEPT SPOILERS ON A FLAT 
PLATE AT MACH NUMBERS OF 1.61 AND 2.01. 
Douglas R. Lord and K. R. Czarnecki. March 1956. 
174p. diagrs., photos., tabs. (NACA RM L55L12) 



LOW-SPEED INVESTIGATION OF THE LATERAL- 
CONTROL CHARACTERISTICS OF A FLAP-TYPE 
SPOILER AND A SPOILER-SLOT-DEFLECTOR ON 
A 30° SWEPTBACK WING-FUSELAGE MODEL 
HAVING AN ASPECT RATIO OF 3, A TAPER RATIO 
OF 0.5, AND NACA 65A004 AIRFOIL SECTION. 
Alexander D. Hammond, August 1956. 2bp. diagrs., 
tab. (NACA RM L56F18) 



INVESTIGATION OF SPOILER-SLOT-DEFLECTOR 
AILERONS AND OTHER SPOILER AILERONS ON A 
45° SWEPTBACK -WING-FUSELAGE COMBINATION 
AT MACH NUMBERS FROM 0. 60 TO 1.03. F. E. 
West, Jr., Charles F. Whitcomb. and James W. 
Schmeer. September 1956. 59p. diagrs., tab. 
(NACARM L56F15) 



FULL-SCALE WIND-TUNNEL TESTS OF A 35° 
SWEPTBACK-WING AIRPLANE WITH HIGH- 
VELOCITY BLOWING OVER THE TRAILING-EDGE 
FLAPS - LONGITUDINAL AND LATERAL STABIL- 
ITY AND CONTROL. William H. Tolhurst, Jr., 
and Mark W. Kelly. October 1956. 64p. diagrs., 
photo., tabs. (NACA RM A56E24) 



A LOW -SPEED INVESTIGATION OF A HIGH-LIFT 
LATERAL-CONTROL DEVICE CONSISTING OF A 
SPOILER-SLOT-DEFLECTOR AND A TRAILING- 
EDGE FLAP ON A TAPERED 45° SWEPTBACK 
WING. Alexander D. Hammond and Jarrett K. 
Huffman. October 1956. 21p. diagrs. 
(NACA RM L56H31) 



INVESTIGATION OF DEFLECTORS AS GUST ALLE- 
VIATORS ON A 0.09 -SCALE MODEL OF THE BELL 
X-5 AIRPLANE WITH VARIOUS WING SWEEP 
ANGLES FROM 20° TO 60© AT MACH NUMBERS 
FROM 0.40 TO 0.90. Delwin R. Croom and Jarrett 
K. Huffman. November 1957. 28p. diagrs. 
(NACA TN 4175) 



LOW -SUBSONIC INVESTIGATION TO DETERMINE 
THE CHORDWISE PRESSURE DISTRIBUTION AND 
EFFECTIVENESS OF SPOILERS ON A THIN, LOW- 
ASPECT-RATIO, UNSWEPT, UNTAPERED, SEMI- 
SPAN WING AND ON THE WING WITH I.EADINO- 
AND TRAILING-EDGE FLAPS. Delwin R. Croom, 
April 1958. 133p. diagrs., tabs. 
(NACA RM L58B05) 



(1.2.2.4.3) 

All -Movable 



INVESTIGATION OF THE AERODYNAMIC EFFECTS 
OF AN EXTERNAL STORE IN COMBINATION WITH 
60° DELTA AND LOW-ASPECT-RATIO TAPERED 
WINGS AT A MACH NUMBER OF 1.9. Ellery B, 
May, Jr. January 9, 1951. 46p. diagrs., photos. 
(NACA RM L50K03) 



WING -ON AND WING -OFF LONGITUDINAL CHAR- 
ACTERISTICS OF AN AIRPLANE CONFIGURATION 
HAVING A THIN UNSWEPT TAPERED WING OF 
ASPECT RATIO 3, AS OBTAINED FROM ROCKET- 
PROPELLED MODELS AT MACH NUMBERS FROM 
0.8 TO 1.4. Clarence L. Gillis and A- James Vitale. 
March 14, 1951. 52p. diagrs., photos., tabs. 
(NACA RM L50K16) 



LONGITUDINAL STABILITY AND DRAG CHARAC- 
TERISTICS AT MACH NUMBERS FROM 0.75 TO 1.5 
OF AN AIRPLANE CONFIGURATION HAVING A 60° 
SWEPT WING OF ASPECT RATIO 2.24 AS OB- 
TAINED FROM ROCKET -PROPELLED MODELS. 
A. James Vitale, John C. McFall, Jr., and John D. 
Morrow. April 1952. 43p. diagrs., photos., tabs. 
(NACA RM L51K06) 



LONGITUDINAL AERODYNAMIC CHARACTERISTICS 
OF MODEL AIRPLANE CONFIGURATION EQUIPPED 
WITH A SCALED X-l AIRPLANE WING . James H . 
Parks. April 1952. 37p. diagrs. 
(NACARM L51L10a) 



PERFORMANCE CHARACTERISTICS OF CANARD- 
TYPE MISSILE WITH VERTICALLY MOUNTED 
NACELLE ENGINES AT MACH NUMBERS 1.5 TO 
2.0. Leonard J. Obery and Howard S. Krasnow. 
September 1952. 25p. diagrs. (NACA RM E52H08) 



PERFORMANCE CHARACTERISTICS OF CANARD- 
TYPE MISSILE WITH WING-MOUNTED NACELLE 
ENGINES AT MACH NUMBERS 1.5 TO 2.0. Emil J. 
Kremzier and Joseph Davids. November 1952. 
30p. diagrs., tab. (NACA RM E52J08) 



TOTAL -PRESSURE AND SCHLIEREN STUDIES OF 
THE WAKES OF VARIOUS CANARD CONTROL SUR- 
FACES MOUNTED ON A MISSILE BODY AT A MACH 
NUMBER OF 1.93. William B. Boatrlght. 
November 1952. 47p. photos., diagrs. 
(NACA RM L52I29) 



55 



(1) AERODYNAMICS 



LIFT, DRAG, AND HINGE MOMENTS AT SUPER- 
SONIC SPEEDS OF AN ALL-MOVABLE TRIANGULAR 
WING AND BODY COMBINATION. William C. Drake. 
September 1953. 38p. diagrs., photos., tabs. 
(NACA RM A53F22) 



COMPONENT TESTS TO DETERMINE THE AERO- 
DYNAMIC CHARACTERISTICS OF AN ALL- 
MOVABLE 70^ DELTA CANARD-TYPE CONTROL 
IN THE PRESENCE OF A BODY AT A MACH NUM- 
BER OF 1.61. M. Leroy Spearman. October 1953". 
30p. diagrs., tabs. (NACA RM L53I03) 



A METHOD FOR ESTIMATING THE ROLLING MO- 
MENTS CAUSED BY WING-TAIL INTERFERENCE 
FOR MISSILE AT SUPERSONIC SPEEDS. Sherman 
Edwards and Katsu mi Hikido . November 1953. 68p. 
diagrs., tabs. (NACA RM A53H18) 



EFFECT OF LARGE DEFLECTIONS OF A CANARD 
CONTROL AND DEFLECTIONS OF A WING-TIP 
CONTROL ON THE STATIC -STABILITY AND 
INDUCED-ROLL CHARACTERISTICS OF A CRUCI- 
FORM CANARD MISSILE AT A MACH NUMBER OF 
2.01. M. Leroy Spearman. December 1953. 20p. 
diagrs., tabs. (NACA RM L53K03) 



EFFECTS OF LEADING-EDGE CHORD EXTENSIONS 
AND AN ALL-MOVABLE HORIZONTAL TAIL ON 
THE AERODYNAMIC CHARACTERISTICS OF A 
WING -BODY COMBINATION EMPLOYING A TRI- 
ANGULAR WING OF ASPECT RATIO 3 MOUNTED IN 
A HIGH POSITION AT SUBSONIC AND SUPERSONIC 
SPEEDS. Benton E. Wetzel and Frank A. Pfyl. 
January 1954. 35p. diagrs., photo., tabs. 
(NACA RM A53jl4a) 



AERODYNAMIC CHARACTERISTICS OF A 
CRUCIFORM -WING MISSILE WITH CANARD CON- 
TROL SURFACES AND OF SOME VERY SMALL 
SPAN WING-BODY MISSILES AT A MACH NUMBER 
OF 1.41. M. Leroy Spearman and Ross B. 
Robinson. April 1954. 27p. diagrs., tabs. 
(NACA RM L54B11) 



WIND-TUNNEL INVESTIGATION AT A MACH NUM- 
BER OF 2.01 OF THE AERODYNAMIC CHARACTER- 
ISTICS IN COMBINED PITCH AND SIDESLIP OF 
SOME CANARD-TYPE MISSILES HAVING CRUCI- 
FORM WINGS AND CANARD SURFACES WITH 70° 
DELTA PLAN FORMS. M. Leroy Spearman and 
Cornelius Driver. August 1954. 121p. diagrs., 
tabs. (NACA RM L54F09) 



AERODYNAMIC CHARACTERISTICS AT A MACH 
NUMBER OF 2.01 OF TWO CRUCIFORM MISSILE 
CONFIGURATIONS HAVING 70° DELTA WINGS 
WITH LENGTH-DIAMETER RATIOS OF 14.8 AND 
17.7 WITH SEVERAL CANARD CONTROLS. 
M. Leroy Spearman and Ross B. Robinson. August 
1954. 32p. diagrs., tabs. (NACA RM L54G20) 



SOME EFFECTS OF AILERON SPAN, AILERON 
CHORD, AND WING TWIST ON ROLLING EFFEC- 
TIVENESS AS DETERMmED BY ROCKET- 
POWERED MODEL TESTS AND THEORETICAL 
ESTIMATES. H. Kurt Strass and Warren A. Tucker. 
September 1954. 29p. diagrs., photos., tabs. 
(NACA RM L54G13) 



FREE- FLIGHT INVESTIGATION, INCLUDING 
SOME EFFECTS OF WING AEROELASTICITY, OF 
THE ROLLING EFFECTIVENESS OF AN ALL- 
MOVABLE HORIZONTAL TAIL WITH DIFFEREN- 
TIAL INCIDENCE AT MACH NUMBERS FROM 0.6 
TO 1.5. Roland D. English. January 1955. Up. 
diagrs., photo. (NACA RM L54K30) 



COLLECTION AND SUMMARY OF FLAP-TYPE- 
AILERON ROLLING -EFFECTIVE NESS DATA AT 
ZERO LIFT AS DETERMINED BY ROCKET- 
POWERED MODEL TESTS AT MACH NUMBERS 
BETWEEN 0.6 AND 1.6. H. Kurt Strass, Emily W. 
Stephens, E. M. Fields, and Eugene D. Schult. 
September 1955. 95p. diagrs., photos., tabs. 
(NACA RM L55F14) 



FREE-FLIGHT INVESTIGATION OF THE CONTROL 
EFFECTIVENESS OF A DIFFERENTIALLY DE- 
FLECTED HORIZONTAL TAIL AT MACH NUMBERS 
FROM 0.8 TO 1.6. Jesse L. Mitchell and A. James 
Vttale. April 1956. 25p. diagrs., photo., tabs. 
(NACA RM L56B20) 



WIND-TUNNEL INVESTIGATION OF A RAM-JET 
MISSILE MODEL HAVING A WING AND CANARD 
SURFACES OF DELTA PLAN FORM WITH 70° 
SWEPT LEADING EDGES. FORCE AND MOMENT 
CHARACTERISTICS AT COMBINED ANGLES OF 
PITCH AND SIDESLIP FOR MACH NUMBER 2.01. 
Cornelius Driver and Clyde V. Hamilton. April 
1956. 67p. diagrs., photo., tabs. 
(NACA RM L56B21) 



LIFT AND CENTER OF PRESSURE OF WING-BODY- 
TAIL COMBINATIONS AT SUBSONIC, TRANSONIC, 
AND SUPERSONIC SPEEDS. William C. Pitts, Jack 
N. Nielsen, and George E. Kaattari. 1957. ii, 70p. 
diagrs., tabs. (NACA Rept. 1307) 



(1.2.2. 5) 
REYNOLDS NUMBER EFFECTS 



A COMPARISON OF THE AERODYNAMIC CHARAC- 
TERISTICS AT TRANSONIC SPEEDS OF FOUR 
WING -FUSELAGE CONFIGURATIONS AS DETER- 
MINED FROM DIFFERENT TEST TECHNIQUES 
Charles J. Donlan, BoydC. Myers. II. and Axel T 
Mattson. October 4, 1950 66p diagrs , photos , 
tabs. (NACA RM L50H02) 



REVIEW OF THE MAXIMUM-LIFT CHARACTER- 
ISTICS OF THIN AND SWEPT WINGS. JohwG. 
Lowry and Jones F. Cahill. June 5, 1951. lOp. 
diagrs. (NACA RM L51E03) 



LIFT, DRAG, AND PITCHING MOMENT OF LOW- 
ASPECT-RATIO WINGS AT SUBSONIC AND SUPER- 
SONIC SPEEDS - TWISTED AND CAMBERED TRI- 
ANGULAR WING OF ASPECT RATIO 2 WITH NACA 
0003-63 THICKNESS DISTRIBUTION. Charles F. 
Hall and John C . Heitmeyer. June 12, 1951. 24p. 
diagrs., photo., tab. (NACA RM A51E01) 



56 



(1) AERODYNAMICS 



LIFT, DRAG, AND PITCHING MOMENT OF LOW- 
ASPECT-RATIO WINGS AT SUBSONIC AND SUPER- 
SONIC SPEEDS - TWISTED AND CAMBERED TRI- 
ANGULAR WING OF ASPECT RATIO 2 WITH NACA 
0005-63 THICKNESS DISTRIBUTION. John C. 
Heitmeyer and Robert B. Petersen. April 1952. 
20p. diagrs., tabs. (NACA RM A52B08) 



THE AERODYNAMIC CHARACTERISTICS OF A 
SUPERSONIC AIRCRAFT CONFIGURATION WITH A 
40° SWEPTBACK WING THROUGH A MACH NUM- 
BER RANGE FROM TO 2.4 AS OBTAINED FROM 
VARIOUS SOURCES. M. Leroy Spearman and Ross 
B. Robinson. April 1952. 50p. diagrs., photo., 
tab. (NACA RM L52A21) 



EFFECT OF LEADING-EDGE CHORD-EXTENSIONS 
ON SUBSONIC AND TRANSONIC AERODYNAMIC 
CHARACTERISTICS OF THREE MODELS HAVING 
45° SWEPTBACK WINGS OF ASPECT RATIO 4. 
Kenneth W. Goodson and Albert G. Few, Jr. 
January 1953. 31p. diagrs., photos., tab. 
(NACA RM L52K21) 



LIFT, DRAG, AND PITCHING MOMENT OF LOW- 
ASPECT-RATIO WINGS AT SUBSONIC AND SUPER- 
SONIC SPEEDS. Charles F. Hall. April 1953. 
132p. diagrs., tabs. (NACA RM A53A30) 



COMPARISON OF THE AERODYNAMIC CHARACTER- 
ISTICS AT TRANSONIC SPEEDS OF A PLANE WING 
AND A CAMBERED AND TWISTED WING, BOTH 
HAVING 45° OF SWEEPBACK AND AN ASPECT 
RATIO OF 6. George H. Holdaway. May 1953. 
49p. diagrs., photos. (NACA RM A53B16) 



LONGITUDINAL CHARACTERISTICS OF WINGS. 

Thomas A. Toll. October 1953. 18p. diagrs. 
(NACA RM L53I21b) 



DRAG DUE TO LIFT AT MACH NUMBERS UP TO 2.0. 
Edward C. Polhamus. November 1953. 18p. diagrs. 
(NACA RM L53IZ2b) 



LONGITUDINAL STABILITY CHARACTERISTICS 
AT MACH NUMBERS UP TO 0.92 OF A WING- 
BODY-TAIL COMBINATION HAVING A WING WITH 
45° OF SWEEPBACK AND A TAIL IN VARIOUS 
VERTICAL POSITIONS. Jack D. Stephenson, 
Angelo Bandettini, and Ralph Selan. January 1955. 
64p. diagrs., photos., tabs. (NACA RM A54K09) 



EFFECTS OF INCREASING REYNOLDS NUMBER 
FROM 2 x 106 TO 6 x 106 ON THE AERODYNAMIC 
CHARACTERISTICS AT TRANSONIC SPEEDS OF A 
45" SWEPT WING WITH 60 LEADING-EDGE DROOP. 
James W. Schmeer and J . Lawrence Cooper. 
February 1955. 22p. diagrs., photo. 
(NACA RM L54L10) 



INVESTIGATION OF INTERFERENCE LIFT, DRAG, 
AND PITCHING MOMENT OF A SERIES OF TRI- 
ANGULAR WING AND BODY COMBINATIONS AT A 
MACH NUMBER OF 1.62. Donald E. Coletti. May 
1955. 49p. diagrs., photo., tabs. 
(NACA RM L55B25) 



INVESTIGATION OF THE EFFECTS OF AN AIRFOIL 
SECTION MODIFICATION ON THE AERODYNAMIC 
CHARACTERISTICS AT SUBSONIC AND SUPERSONIC 
SPEEDS OF A THIN SWEPT WING OF ASPECT 
RATIO 3 IN COMBINATION WITH A BODY. David 
Graham and William T . Evans . June 1955. 46p. 
diagrs., tabs. (NACA RM A55D11) 



A COMPARISON AT MACH NUMBERS UP TO 0.92 
OF THE CALCULATED AND EXPERIMENTAL 
DOWNWASH AND WAKE CHARACTERISTICS AT 
VARIOUS HORIZONTAL TAIL HEIGHTS BEHIND A 
WING WITH 45° OF SWEEPBACK. Jack D. 
Stephenson, Ralph Selan, and Angelo Bandettini. 
June 1955. 81p. diagrs., photos., tabs. 
(NACA RM A55D27a) 



EFFECTS OF LEADING-EDGE RADIUS ON THE 
LONGITUDINAL STABILITY OF TWO 45° SWEPT- 
BACK WINGS INCORPORATING LEADING-EDGE 
CAMBER AS INFLUENCED BY REYNOLDS NUM- 
BERS UP TO 8.00 x 10 6 AND MACH NUMBERS UP 
TO 0.290. Gerald V. Foster. October 1955. 44p. 
diagrs. (NACA RM L55H04) 



A STUDY OF CONICAL CAMBER FOR TRIANGULAR 
AND SWEPTBACK WINGS. John W. Boyd, Eugene 
Migotsky, and Benton E. Wetzel. November 1955. 
79p. diagrs., tabs. (NACA RM A55G19) 



EFFECT OF LEADING-EDGE SWEEPBACK ON LIFT, 
DRAG, AND PITCHING-MOMENT CHARACTERIS- 
TICS OF THIN WINGS OF ASPECT RATIO 3 AND 
TAPER RATIO 0.4 AT SUBSONIC AND SUPERSONIC 
SPEEDS. Benton E. Wetzel. November 1955 . 22p. 
diagrs., tabs. (NACA RM A55H04a) 



INVESTIGATION OF INTERFERENCE LIFT, DRAG, 
AND PITCHING MOMENT OF A SERIES OF 
TRIANGULAR-WING AND BODY COMBINATIONS 
AT A MACH NUMBER OF 1.94. Donald E. Coletti. 
December 1955. 52p. diagrs., photo., tabs. 
(NACA RM L55I14) 



EFFECTS OF LEADING-EDGE RADIUS ON THE 
LONGITUDINAL STABILITY CHARACTERISTICS OF 
TWO 60° SWEPTBACK WINGS AT HIGH REYNOLDS 
NUMBERS. William C. Schneider. March 1956. 
46p. diagrs. (NACA RM L55L30) 



EFFECTS OF REYNOLDS NUMBER AND LEADING- 
EDGE SHAPE ON THE LOW-SPEED LONGITUDINAL 

STABILITY OF A 6-PERCENT-THICK 450 SWEPT- 
BACK WING. William C. Schneider. April 1956. 
32p. diagrs. (NACA RM L56B14) 



DATA FROM LARGE-SCALE LOW-SPEED TESTS 
OF AIRPLANE CONFIGURATIONS WITH A THIN 45° 
SWEPT WING INCORPORATING SEVERAL 
LEADING-EDGE CONTOUR MODIFICATIONS. 

William T. Evans. May 1956. HOp. diagrs., 
photo-, tabs. (NACA RM A56B17) 



THE EFFECT OF CONICAL CAMBER ON THE 
STATIC LONGITUDINAL, LATERAL, AND DIREC- 
TIONAL CHARACTERISTICS OF A 45° SWEPTBACK 
WING AT MACH NUMBERS UP TO 0.96. Robert I. 
Sammonds and Robert M. Reynolds. July 1956. 
64p. diagrs., tabs. (NACA RM A56D02) 



57 



( 1 ) AERODYNAMICS 



EFFECT OF A FUSELAGE ON THE LOW-SPEED 
LONGITUDINAL AERODYNAMIC CHARACTERISTICS 
OF A 450 SWEPTBACK WING WITH DOUBLE 
SLOTTED FLAPS. Rodger L. Naeseth. September 
1956. 31p. diagrs., tabs. {NACA RM L56G02) 



A SUMMARY AND ANALYSIS OF THE LOW -SPEED 
LONGITUDINAL CHARACTERISTICS OF SWEPT 
WINGS AT HIGH REYNOLDS NUMBER. G. Chester 
Furlong and James G. McHugh. 1957. iii, 149p. 
diagrs., tabs. (NACA Rept. 1339. Supersedes 
RM L52D16) 



THE SUBSONIC STATIC AERODYNAMIC CHARAC- 
TERISTICS OF AN AIRPLANE MODEL HAVING A 
TRIANGULAR WING OF ASPECT RATIO 3. I - EF- 
FECTS OF HORIZONTAL-TAIL LOCATION AND 
SIZE ON THE LONGITUDINAL CHARACTERISTICS. 
Bruce E. Tinling and Armando E. Lopez. July 1957. 
85p. diagrs., photo., tabs. (NACA TN 4041. Super- 
sedes RM A53L15) 



EFFECTS OF FIXING BOUNDARY-LAYER TRANSI- 
TION FOR AN UNSWEPT-WING MODEL AND AN 
EVALUATION OF POROUS TUNNEL-WALL INTER- 
FERENCE FOR MACH NUMBERS FROM 0.60 TO 
1.40. Louis S. Stivers, Jr., and Garth W. Lippmann. 
April 1958. 37p. diagrs. (NACA TN 4228) 



EFFECTS OF FIXING TRANSITION ON THF TRAN- 
SONIC AERODYNAMIC CHARACTERISTICS OF A 
WING -BODY CONFIGURATION AT REYNOLDS NUM- 
BERS FROM 2.4 TO 12 MILLION. Lynn W. Hunton. 
July 1958. 56p. diagrs. (NACA TN 4279) 



IDEALIZED WINGS AND WING-BODIES AT A MACH 
NUMBER OF 3. Elliott D. Katzen. July 1958. lip. 
diagrs. (NACA TN 4361) 



THE STATIC LONGITUDINAL CHARACTERISTICS 
OF A TWISTED AND CAMBERED 45° SWEPTBACK 
WING AT MACH NUMBERS UP TO 0.96. Robert I. 
Sammonds and Robert M. Reynolds. August 1958. 
26p. diagrs., tab. (NACA RM A58C21) 



THE EFFECTS OF AN INVERSE-TAPER LEADING- 
EDGE FLAP ON THE AERODYNAMIC CHARACTER- 
ISTICS IN PITCH OF A WING-BODY COMBINATION 
HAVING AN ASPECT RATIO OF 3 AND 45<> OF 
SWEEPBACK AT MACH NUMBERS TO 0.92. Fred A. 
Demele and K. Harmon Powell. August 1958. 57p. 
diagrs., photo., tabs. (NACA TN 4366) 



(1.2.2.6) 

MACH NUMBER EFFECTS 



SUPERSONIC-TUNNEL TESTS OF TWO SUPER- 
SONIC AIRPLANE MODEL CONFIGURATIONS. 
Macon C. Ellis, Jr., Lowell E. Hasel, and Carl E. 
Grigsby. December 31, 1947. 49p. diagrs., 
photos., tab. (NACA RM L7J15) 



RESULTS OBTAINED DURING EXTENSION OF U.S. 
AIR FORCE TRANSONIC- FLIGHT TESTS OF XS-1 
AIRPLANE. Harold R. Goodman and Hubert M. 
Drake. November 16, 1948. 12p. diagrs. 
(NACA RM L8I28) 



FLIGHT TESTS AT TRANSONIC AND SUPERSONIC 
SPEEDS OF AN AIRPLANE-LIKE CONFIGURATION 
WITH THIN STRAIGHT SHARP-EDGE WINGS AND 
TAIL SURFACES. Clarence L. Gillis and Jesse L. 
Mitchell. January 5, 1949. 37p. diagrs., photos., 
tab. (NACA RM L8K04a) 



ESTIMATED TRANSONIC FLYING QUALITIES OF A 
TAILLESS AIRPLANE BASED ON A MODEL INVES- 
TIGATION. Charles J. Donlan and Richard E . Kuhn. 
June 8, 1949. 63p. diagrs., photos., tabs. 
(NACA RM L9D08) 



AERODYNAMIC STUDY OF A WING-FUSELAGE 
COMBINATION EMPLOYING A WING SWEPT BACK 
630. . EFFECTS AT SUBSONIC SPEEDS OF A 
CONSTANT-CHORD ELEVON ON A WING CAM- 
BERED AND TWISTED FOR A UNIFORM LOAD AT 
A LIFT COEFFICIENT OF 0.25. J. Lloyd Jones and 
Fred A. Demele. December 5, 1949. 44p. diagrs., 
photos., tab. (NACA RM A9I27) 



THE EFFECTS OF SCALE AND TEST TECHNIQUE 
ON THE VALIDITY OF SMALL-SCALE MEASURE- 
MENTS OF THE AERODYNAMIC CHARACTERISTICS 
OF A WING WITH THE LEADING EDGE SWEPT 
BACK 630. l. Stewart Rolls. December 9, 1949. 
20p. diagrs., photos. (NACA RM A9J06) 



WIND-TUNNEL TESTS OF A 0.1 6 -SCALE MODEL 
OF THE X-3 AIRPLANE AT HIGH SUBSONIC 
SPEEDS. STABILITY AND CONTROL CHARACTER- 
ISTICS. William T. Hamilton and Joseph W. Cleary. 
April 21, 1950. 129p. diagrs., photos., tabs. 
(NACA RM A50A03) 



WIND-TUNNEL TESTS OF A 0.16-SCALE MODEL 
OF THE X-3 AIRPLANE AT HIGH SUBSONIC SPEEDS. 
- ADDITIONAL STABILITY AND CONTROL CHAR- 
ACTERISTICS AND THE AERODYNAMIC EFFECTS 
OF EXTERNAL STORES AND RAM JETS. • Joseph W. 
Cleary and Jack A. Mellenthin. June 13, 1950. 86p. 
diagrs., photos., tabs. (NACA RM A50C30) 



WIND-TUNNEL TESTS OF A 0.16-SCALE MODEL 
OF THE X-3 AIRPLANE AT HIGH SUBSONIC SPEEDS. 
- WING AND FUSELAGE PRESSURE DISTRIBUTION. 
Joseph W. Cleary and Jack A. Mellenthin. June 22, 
1950. 6 lp. diagrs., photos. (NACA RM A50D07) 



FLIGHT MEASUREMENTS WITH THE DOUGLAS 
D-558-II (BUAERO NO. 37974) RESEARCH AIR- 
PLANE. DETERMINATION OF THE AERODYNAMIC 
CENTER AND ZERO-LIFT PITCHING-MOMENT 
COEFFICIENT OF THE WING-FUSELAGE COMBI- 
NATION BY MEANS OF TAIL-LOAD MEASURE- 
MENTS IN THE MACH NUMBER RANGE FROM 
0.37 TO 0.87. John P. Mayer, George M. Valentine, 
and Geraldine C. Mayer. July 11, 1950. 27p. 
diagrs., photos., tab. (NACA RM L50D10) 



A COMPARISON OF THE AERODYNAMIC CHARAC- 
TERISTICS AT TRANSONIC SPEEDS OF FOUR 
WING-FUSELAGE CONFIGURATIONS AS DETER- 
MINED FROM DIFFERENT TEST TECHNIQUES 
Charles J. Donlan, BoydC. Myors. II. nnd Axel T 
Mattson. October 4, 1950 66p diaprs . photos ., 
tabs. (NACA RM L 50 HO 2) 



58 



(1) AERODYNAMICS 



PRELIMINARY RESULTS OF THE FLIGHT INVES- 
TIGATION BETWEEN MACH NUMBERS OF 0.80 AND 
1.36 OF A ROCKET-POWERED MODEL OF A 
SUPERSONIC AIRPLANE CONFIGURATION HAVING 
A TAPERED WING WITH CIRCULAR-ARC SECTIONS 
AND 40° SWEEPBACK. Charles T. D'Aiutolo and 
Homer P. Mason. October 31, 1950. 30p. diagrs., 
photos., tab. (NACA RM L50H29a) 



DETERMINATION OF LONGITUDINAL STABILITY 
OF THE BELL X-l AIRPLANE FROM TRANSIENT 
RESPONSES AT MACH NUMBERS UP TO 1.12 AT 
LIFT COEFFICIENTS OF 0.3 AND 0.6. Ellwyn E. 



22p diagrs. (NACA RM L50I06a) 



AN INVESTIGATION OF THE LONGITUDINAL 
CHARACTERISTICS OF THE X-3 CONFIGURATION 
USING ROCKET-PROPELLED MODELS. PRELIMI- 
NARY RESULTS AT MACH NUMBERS FROM 0.65 
TO 1.25. Jesse L. Mitchell and Robert F. Peck. 
December 1, 1950. 30p. diagrs., photos. 
(NACA RM L50J03) 



FLIGHT MEASUREMENTS WITH THE DOUGLAS 
D-558-II (BUAERO NO. 37974) RESEARCH AIR- 
PLANE. MEASUREMENTS OF WING LOADS AT 
MACH NUMBERS UP TO 0.87. John P. Mayer, 
George M. Valentine, and Beverly J. Swanson. 
December 26, 1950. 35p. diagrs., photos., tab. 
(NACA RM L50H16) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR-ARC SECTIONS AND 40° SWEEPBACK. 
FORCE CHARACTERISTICS OF THE COMPLETE 
CONFIGURATION AND ITS VARIOUS COMPONENTS 
AT MACH NUMBERS OF 1.40 AND 1.59. Norman F. 
Smith and Jack E. Marte. January 22, 1951 . 55p. 
diagrs., photos., tab. (NACA RM L50K14) 



WING -ON AND WING-OFF LONGITUDINAL CHAR- 
ACTERISTICS OF AN AIRPLANE CONFIGURATION 
HAVING A THIN UNSWEPT TAPERED WING OF 
ASPECT RATIO 3, AS OBTAINED FROM ROCKET- 
PROPELLED MODELS AT MACH NUMBERS FROM 
0.8 TO 1.4. Clarence L. Gillis and A. James Vitale. 
March 14, 1951. 52p. diagrs., photos., tabs. 
(NACA RM L50K16) 



REVIEW OF THE MAXIMUM-LIFT CHARACTER- 
ISTICS OF THIN AND SWEPT WINGS. John'G. 
Lowry and Jones F. Cahill. June 5, 1951. lOp. 
diagrs. (NACA RM L51E03) 



LIFT, DRAG, AND PITCHING MOMENT OF LOW- 
ASPECT-RATIO WINGS AT SUBSONIC AND SUPER- 
SONIC SPEEDS - TWISTED AND CAMBERED TRI- 
ANGULAR WING OF ASPECT RATIO 2 WITH NACA 
0003-63 THICKNESS DISTRIBUTION. Charles F. 
Hall and John C. Heitmeyer. June 12, 1951. 24p. 
diagrs., photo., tab. (NACA RM A51E01) 



AN INVESTIGATION OF THE LONGITUDINAL CHAR- 
ACTERISTICS OF THE X-3 CONFIGURATION WITH 
WING AND HORIZONTAL TAIL SURFACES OF 
ASPECT RATIO 3.0 BY MEANS OF ROCKET- 
PROPELLED MODELS. RESULTS AT HIGH LIFT 
COEFFICIENTS. Robert F. Peck and Jesse L. 
Mitchell. August 27, 1951. 34p. diagrs., photos. 
(NACA RM L51G10) 



BASIC PRESSURE MEASUREMENTS ON A FUSE- 
LAGE AND A 45° SWEPTBACK WING-FUSELAGE 
COMBINATION AT TRANSONIC SPEEDS IN THE 
SLOTTED TEST SECTION OF THE LANGLEY 
8-FOOT HIGH-SPEED TUNNEL. Donald L. Loving 
and Claude V. Williams. September 1951. 59p. 
diagrs., photos. (NACA RM L51F05) 



WIND-TUNNEL TESTS OF A l/12-SCALE MODEL 
OF THE X-3 AIRPLANE AT SUBSONIC AND SUPER- 
SONIC SPEEDS. Robert N. Olson and Robert S. 
Chubb. September 14, 1951. lllp. diagrs., photo., 
tabs. (NACA RM A51F12) 



FREE-FLIGHT MEASUREMENTS AT MACH NUM- 
BERS FROM 0.7 TO 1.6 OF SOME EFFECTS OF 
AIRFOIL-THICKNESS DISTRIBUTION AND 
TRAILING-EDGE ANGLE ON AILERON ROLLING 
EFFECTIVENESS AND DRAG FOR WINGS WITH 0° 
AND 45° SWEEPBACK. E. M. Fields and H. Kurt 
Strass. October 1951. 63p. diagrs., photos., tab. 
(NACA RM L51G27) 



ANALYSIS OF LONGITUDINAL STABILITY AND 
TRIM OF THE BELL X-l AIRPLANE AT A LIFT 
COEFFICIENT OF 0.3 TO MACH NUMBERS NEAR 
1.05. Hubert M. Drake, John R. Carden, and 
Harry P. Clagett. October 1951. 30p. diagrs., 
photo., tab. (NACA RM L51H01) 



AN INVESTIGATION AT TRANSOM*. SPEEDS OF 
THE EFFECTS OF THICKNESS RATIO AND OF 
THICKENED ROOT SECTIONS ON THE AERODY- 
NAMIC CHARACTERISTICS OF WINGS WITH 47« 
SWEEPBACK. ASPECT RATIO 3.5, AND TAPER 
RATIO 0.2 IN THE SLOTTED TEST SECTION OF 
THE LANGLEY 8-FOOT HIGH-SPEED TUNNEL. 
Ralph P. Bielat, Daniel E. Harrison, and Domenic A. 
Coppolino. October 1951, 38p. diagrs., photo., tab. 
(NACA RM L51104a) 



FLIGHT DETERMINATION OF THE DRAG AND 
LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A ROCKET-POWERED MODEL 
OF A 60° DELTA-WTNG AIRPLANE FROM MACH 
NUMBERS OF 0.75 TO 1.70. Grady L. Mitcham, 
Norman L. Crabill, and Joseph E. Stevens. 
November 1951. 44p. diagrs., photos., tab. 
(NACA RM L51I04) 



SUMMARY OF SOME EFFECTIVE AERODYNAMIC 
TWISTING-MOMENT COEFFICIENTS OF VARIOUS 
WING-CONTROL CONFIGURATIONS AT MACH 
NUMBERS FROM 0.6 TO 1.7 AS DETERMINED 
FROM ROCKET -POWERED MODELS. H. Kurt 
Strass. January 1952. 22p. diagrs., photo., 
2 tabs. (NACA RM L51K20) 



THE STATIC AND DYNAMIC LONGITUDINAL STA- 
BILITY CHARACTERISTICS OF SOME SUPERSONIC 
AIRCRAFT CONFIGURATIONS. Jesse L. MitcheU. 
January 1952. 19p. diagrs. (NACA RM L52A10a) 



WING LOAD DISTRIBUTION ON A SWEPT-WING 
AIRPLANE IN FLIGHT AT MACH NUMBERS UP TO 
1.11 AND COMPARISON WITH THEORY. L. Stewart 
Rolls and Frederick H. Matteson. April 1952. 73p. 
diagrs., photos,, tabs. (NACA RM A52A31) 



59 



(1 ) AERODYNAMICS 



LIFT, DRAG, AND PITCHING MOMENT OF LOW- 
ASPECT-RATIO WINGS AT SUBSONIC AND SUPER- 
SONIC SPEEDS - TWISTED AND CAMBERED TRI- 
ANGULAR WING OF ASPECT RATIO 2 WITH NACA 
0005-63 THICKNESS DISTRIBUTION. John C . 
Heitmeyer and Robert B. Petersen. April 1952. 
20p. diagrs., tabs. (NACA RM A52B08) 



LONGITUDINAL STABILITY AND DRAG CHARAC- 
TERISTICS AT MACH NUMBERS FROM 0.75 TO 1.5 
OF AN AIRPLANE CONFIGURATION HAVING A 60° 
SWEPT WING OF ASPECT RATIO 2.24 AS OB- 
TAINED FROM ROCKET-PROPELLED MODELS. 
A. James Vitale, John C. McFall, Jr., and John D. 
Morrow. April 1952. 43p. diagrs., photos., tabs. 
(NACA RM L51K06) 



LONGITUDINAL AERODYNAMIC CHARACTERISTICS 
OF MODEL AIRPLANE CONFIGURATION EQUIPPED 
WITH A SCALED X-l AIRPLANE WING. James H. 
Parks. April 1952. 37p. diagrs. 
(NACA RM L51H0a) 



THE AERODYNAMIC CHARACTERISTICS OF A 
SUPERSONIC AIRCRAFT CONFIGURATION WITH A 
40° SWEPTBACK WING THROUGH A MACH NUM- 
BER RANGE FROM TO 2.4 AS OBTAINED FROM 
VARIOUS SOURCES. M. Leroy Spearman and Ross 
B. Robinson. April 1952. 50p. diagrs., photo., 
tab. (NACA RM L52A21) 



AERODYNAMIC LOADING CHARACTERISTICS OF A 
WING-FUSELAGE COMBINATION HAVING A WING 
OF 45° SWEEPBACK MEASURED IN THE LANGLEY 
8-FOOT TRANSONIC TUNNEL. Donald L. Loving 
and Claude V. Williams. May 1952. 58p. diagrs., 
photos . , tab . (N AC A RM L 5 2B 27) 



A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE AERODYNAMIC CHARACTERISTICS OF THREE 
4-PERCENT-THICK WINGS OF SWEEPBACK 
ANGLES 10.80, 35", AND 47°, ASPECT RATIO 3.5, 
AND TAPER RATIO 0.2 IN COMBINATION WITH A 
BODY. Ralph P. Biolat July 1952. 33p. diagrs., 
photos., tab. (NACA RM L52B08) 



PRELIMINARY INVESTIGATION OF THE LOW- 
AMPLITUDE DAMPING IN PITCH OF TAILLESS 
DELTA- AND SWEPT-WING CONFIGURATIONS AT 
MACH NUMBERS FROM 0.7 TO 1.35. Charles T. 
D'Aiutolo and Robert N. Parker. August 1952. 27p. 
diagrs., photos., tab. (NACA RM L52G09) 



FREE-FLIGHT MEASUREMENTS OF SOME EF- 
FECTS OF SPOILER SPAN AND PROJECTION AND* 
WING FLEXIBILITY ON ROLLING EFFECTIVENESS 
AND DRAG OF PLAIN SPOILERS ON A TAPERED 
SWEPTBACK WING AT MACH NUMBERS BETWEEN 
0.6 AND 1.6. Eugene D. SchultandE. M. Fields. 
October 1952. 30p. diagrs., photo., tab. 
(NACA RM L52H06a) 



AERODYNAMIC CHARACTERISTICS EXTENDED TO 
HIGH ANGLES OF ATTACK AT TRANSONIC SPEEDS 
OF A SMALL-SCALE 0° SWEEP WING, 45° SWEPT- 
BACK WING, AND 60° DELTA WING. Harleth G. 
Wiley. November 1952. 26p. diagrs. 
(NACA RM L52I30) 



INVESTIGATION AT HIGH SUBSONIC SPEEDS OF 
BODIES MOUNTED FROM THE WING OF AN 
UNSWEPT-WING-FUSELAGE MODEL, INCLUDING 
MEASUREMENTS OF BODY LOADS. H. Norman 
Silvers and Thomas J. King, Jr. November 1952. 
37p. diagrs., photos., tabs. (NACA RM L52J08) 



EFFECT OF LEADING-EDGE CHORD-EXTENSIONS 
ON SUBSONIC AND TRANSONIC AERODYNAMIC 
CHARACTERISTICS OF THREE MODELS HAVING 
45° SWEPTBACK WINGS OF ASPECT RATIO 4. 
Kenneth W. Goodson and Albert G. Few, Jr. 
January 1953. 31p. diagrs., photos., tab. 
(NACA RM L52K21) 



LONGITUDINAL STABILITY, CONTROL EFFEC- 
TIVENESS, AND DRAG CHARACTERISTICS AT 
TRANSONIC SPEEDS OF A ROCKET -PROPELLED 
MODEL OF AN AIRPLANE CONFIGURATION 
HAVING AN UNSWEPT TAPERED WING OF ASPECT 
RATIO 3.0 AND NACA 65A004.5 AIRFOIL SECTIONS. 
John C. McFall, Jr., and James A. Hollinger. 
January 1953. 30p. diagrs., photos. 
(NACA RM L52L04) 



TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF ASPECT RATIO, SPANWISE 
VARIATIONS IN SECTION THICKNESS RATIO, AND 
A BODY INDENTATION ON THE AERODYNAMIC 
CHARACTERISTICS OF A 45° SWEPTBACK WING- 
BODY COMBINATION. Melvin M. Carmel. 
January 1953. 44p. diagrs., tab. 
(NACA RM L52L26b) 



A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF BODY INDENTATION, AS SPEC- 
IFIED BY THE TRANSONIC DRAG-RISE RULE, ON 
THE AERODYNAMIC CHARACTERISTICS AND 
FLOW PHENOMENA OF A 45° SWEPTBACK- WING- 
BODY COMBINATION. Harold L. Robinson. 
February 1953. 33p. diagrs., photos., tab. 
(NACA RM L52L12) 



SOME MEASUREMENTS OF FLYING QUALITIES OF 
A DOUGLAS D-558-E RESEARCH AIRPLANE DUR- 
ING FLIGHTS TO SUPERSONIC SPEEDS. Herman O. 
Ankenbruck and Theodore E. Dahlen. March 1953. 
25p. diagrs., photos., tab. (NACA RM L53A06) 



LIFT, DRAG, AND PITCHING MOMENT OF LOW- 
ASPECT-RATIO WINGS AT SUBSONIC AND SLPER- 
SONIC SPEEDS. Charles F. Hall. April 1953. 
132p. diagrs., tabs. (NACA RM A53A30) 



COMPARISON OF THE AERODYNAMIC CHARACTER- 
ISTICS AT TRANSONIC SPEEDS OF A PLANE WING 
AND A CAMBERED AND TWISTED WING, BOTH 
HAVING 45° OF SWEEPBACK AND AN ASPECT 
RATIO OF 6. George H. Holdaway. May 1953. 
49p. diagrs., photos. (NACA RM A53B16) 



SOME MEASUREMENTS OF THE BUFFET REGION 
OF A SWEPT-WING RESEARCH AIRPLANE DURING 
FLIGHTS TO SUPERSONIC MACH NUMBERS. 
Thomas F. Baker. May 1953. 14p. diagrs., 
photos., tab. (NACA RM L53D06) 



60 



(1) AERODYNAMICS 



LOADS DUE TO FLAPS AND SPOILERS ON SWEPT- 
BACK WINGS AT SUPERSONIC AND TRANSONIC 
SPEEDS. Alexander D. Hammond and F. E. West. 
Jr. June 1953. 17p. diagrs. (NACA RM L53D29a) 



THE INFLUENCE OF A CHANGE IN BODY SHAPE 
ON THE EFFECTS OF TWIST AND CAMBER AS 
DETERMINED BY A TRANSONIC WIND-TUNNEL 
INVESTIGATION OF A 45° SWEPTBACK WING- 
FUSELAGE CONFIGURATION. Daniel E. Harrison. 
August 1953. 23p. diagrs., tab. 
(NACARM L53B03) 



A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF BODY INDENTATION ON THE 
AERODYNAMIC CHARACTERISTICS OF AN 
APPROXIMATE -DELTA- WING -BODY CONFIGURA- 
TION, AND A COMPARISON WITH A WING OF 
REVERSED PLAN FORM. Claude V. Williams. 
August 1953. 36p. diagrs., photos., tabs. 
(NACA RM L53F05a) 



A ROCKET-MODEL INVESTIGATION OF THE LON- 
GITUDINAL STABILITY, LIFT, AND DRAG CHAR- 
ACTERISTICS OF THE DOUGLAS X-3 CONFIGURA- 
TION WITH HORIZONTAL TAIL OF ASPECT RATIO 
4.33. Robert F. Peck and James A. Hollinger. 
August 1953. 33p. diagrs., photos. 
(NACA RML53F19a) 



EFFECTS OF LEADING-EDGE SLATS ON THE 
AERODYNAMIC CHARACTERISTICS OF A 45° 
SWEPTBACK WING-FUSELAGE CONFIGURATION 
AT MACH NUMBERS OF 0.4 TO 1.03. Jack F. 
Runrkel and Seymour Steinberg. August 1953. 50p. 
diagrs-, photos. (NACARM L53F23) 



TRANSONIC FLIGHT MEASUREMENT OF THE 
AERODYNAMIC LOAD ON THE EXTENDED SLAT 
OF THE DOUGLAS D-558-II RESEARCH AIRPLANE. 
James R. Peele. August 1953. 34p. diagrs., 
photos., tab. (NACA RM L53F29) 



INVESTIGATION OF WING FLUTTER AT TRAN- 
SONIC SPEEDS FOR SDC SYSTEMATICALLY VARIED 
WING PLAN FORMS. George W. Jones, Jr., and 
Hugh C. DuBose. August 1953. 32p. diagu., 
photos., 3 tabs. (NACA RM L53G10a) 



NOTES ON DAMPING IN ROLL AND LOAD DISTRI- 
BUTIONS IN ROLL AT HIGH ANGLES OF ATTACK 
AND HIGH SUBSONIC SPEED. Richard E. Kuhn. 
August 1953. 18p. diagrs., tab. 
(NACA RM L53G13a) 



A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECT OF MODIFICATIONS TO AN IN- 
DENTED BODY IN COMBINATION WITH A 45<> 
SWEPTBACK WING. Donald L. Loving. September 
1953. 29p. diagrs., photos., tabs. 
(NACA RM L53F02) 



INVESTIGATION OF SPOILER AILERONS WITH AND 
WITHOUT A GAP BEHIND THE SPOILER ON A 45° 
SWEPTBACK WING-FUSELAGE COMBINATION AT 
MACH NUMBERS FROM 0.60 TO 1.03. F. E. West, 
Jr., William Solomon, and Edward M. Brummal. 
Seotember 1953. 38p. diagrs. (NACA RM L53G07a) 



COMPARISON OF THEORETICAL AND EXPERI- 
MENTAL ZERO-LIFT DRAG-RISE CHARACTERIS- 
TICS OF WING -BODY -TAIL COMBINATIONS NEAR 
THE SPEED OF SOUND. George H. Holdaway. 
October 1953. 27p. diagrs., tab. 
(NACA RM A53H17) 



SUBSONIC AND SUPERSONIC HINGE -MOMENT AND 
EFFECTIVENESS CHARACTERISTICS OF AN UN- 
BALANCED LATERAL CONTROL HAVING LOW 
THEORETICAL HINGE MOMENTS AT SUPERSONIC 
SPEEDS. Kenniih L. Coin and William E. Palmer. 
October 1953. 55p. diagrs., photos. 
(NACA RM L53G31a) 



INVESTIGATION OF THE EFFECT OF SPANWISE 
POSITIONING OF A VERTICALLY SYMMETRIC 
OGIVE -CYLINDER NACELLE ON THE HIGH-SPEED 
AERODYNAMIC CHARACTERISTICS OF A 45° 
SWEPTBACK TAPERED-IN-THICKNESS WING OF 
ASPECT RATIO 6 WITH AND WITHOUT A FUSE- 
LAGE. H. Norman Silvers and Thomas J . King, Jr. 
October 1953. 62p. diagrs., tabs. 
(NACARM L53H17) 



RELATIONSHIP OF FLOW OVER A 4 5" SWEPT- 
BACK WING WITH AND WITHOUT LEADING-EDGE 
CHORD-EXTENSIONS TO LONGITUDINAL STABIL- 
ITY CHARACTERISTICS AT MACH NUMBERS FROM 
0.60 TO 103. F E. West. Jr . and James H 
Henderson. October 1953. 47p. diagrs . photos. 
(NACA RM L53Hl8b) 



ROCKET-MODEL INVESTIGATION TO DETERMINE 
THE HINGE -MOMENT AND NORMAL -FORCE 
PROPERTIES OF A FULL -SPAN, CONSTANT- 
CHORD, PARTIALLY BALANCED TRAILING-EDGE 
CONTROL ON A 60° CLIPPED DELTA WING BE- 
TWEEN MACH NUMBERS OF 0.50 AND 1.26. 
C. William Martz and John W. Goslee. October 
1953. 33p. diagrs., photos., tab. 
(NACA RM L53I04) 



LONGITUDINAL CHARACTERISTICS OF WINGS. 
Thomas A. Toll. October 1953. 18p. diagrs. 
(NACA RM L53I21b) 



DATA ON SPOILER-TYPE AILERONS. 
Lowry. October 1953. 27p. diagrs. 
(NACA RM L5 3124a) 



AN ENGINEERING METHOD FOR THE DETER- 
MINATION OF AEROELASTIC EFFECTS UPON THE 
ROLLING EFFECTrVENESS OF AILERONS ON 
SWEPT WINGS. H. Kurt Strass and Emily W. 
Stephens. November 1953. 82p. diagrs., tabs. 
(NACA RM L53H14) 



SOME MEASUREMENTS OF BUFFETING ENCOUN- 
TERED BY A DOUGLAS D-558-H RESEARCH AIR- 
PLANE IN THE MACH NUMBER RANGE FROM 0.5 
TO 0.95. Thomas F. Baker. November 1953 . 22p. 
diagrs., photos., tabs. (NACARM L53I17) 



61 



(1) AERODYNAMICS 



STATIC LONGITUDINAL STABILITY AND CONTROL 
CHARACTERISTICS OF A l/16-SCALE MODEL OF 
THE DOUGLAS D-558-H RESEARCH AIRPLANE AT 
MACK NUMBERS OF 1.61 AND 2.01. M. Leroy 
Spearman. November 1953. 34p. diagrs., tabs. 
(NACA RM L53I22) 



DRAG DUE TO LIFT AT MACH NUMBERS UP TO 2.0. 
Edward C. Polhamus. November 1953. 13p. diagrs. 
(NAC/ RM L53I22b) 



AN INVESTIGATION OF THE TRANSONIC AREA 
RULE BY FLIGHT TESTS OF A SWEPTBACK WING 
ON A CYLINDRICAL BODY WITH AND WITHOUT 
BODY INDENTATION BETWEEN MACH NUMBERS 
0.9 AND 1.8. Sherwood Hoffman. December 1953. 
24p. diagrs., photos., tabs. (NACA RM L53J 20a) 



EFFECTS OF LEADING-EDGE CHORD EXTENSIONS 
AND AN ALL -MOVABLE HORIZONTAL TAIL ON 
THE AERODYNAMIC CHARACTERISTICS OF A 
WING-BODY COMBINATION EMPLOYING A TRI- 
ANGULAR WING OF ASPECT RATIO 3 MOUNTED IN 
A HIGH POSITION AT SUBSONIC AND SUPERSONIC 
SPEEDS. Benton E. Wetzel and Frank A. Pfyl. 
January 1954. 35p. diagrs., photo., tabs. 
(NACARM A53J14a) 



LONGITUDINAL STABILITY CHARACTERISTICS 
AT TRANSONIC SPEEDS OF A ROCKET- 
PROPELLED MODEL OF AN AIRPLANE CON- 
FIGURATION HAVING A 450 SWEPT WING OF 
ASPECT RATIO 6.0. John C. McFall, Jr. 
January 1954. 34 p. diagrs., photos. 
(NACA RM L53G22a) 



DETERMINATION OF LONGITUDINAL STABILITY 
IN SUPERSONIC ACCELERATED MANEUVERS FOR 
THE DOUGLAS D-558-H RESEARCH AIRPLANE. 
Herman O. Ankenbruck. February 1954. 29p. 
diagrs., photos., tab. (NACARM L53J20) 



MEASURED DATA PERTAINING TO BUFFETING AT 
SUPERSONIC SPEEDS OF THE DOUGLAS D-558-II 
RESEARCH AIRPLANE. Thomas F. Baker. 
February 1954. I6p. diagrs., photos., tab. 
(NACA RM L53L10) 



EFFECT OF WING SLATS AND INBOARD WING 
FENCES ON THE LONGITUDINAL STABILITY 
CHARACTERISTICS OF THE DOUGLAS D-558-II 
RESEARCH AIRPLANE IN ACCELERATED MANEU- 
VERS AT SUBSONIC AND TRANSONIC SPEEDS. 
Jack Fischel. February 1954. 125p. diagrs., 
photos., tabs. (NACA RM L53L16) 



EFFECT OF NOSE SHAPE AND TRAILING-EDGE 
BLUNTNESS ON THE AERODYNAMIC CHARACTER- 
ISTICS OF AN UNSWEPT WING OF ASPECT RATIO 
3.1, TAPER RATIO 0.4. AND 3-PERCENT THICK- 
NESS. John C. Heitmever. March 1954. 36p. 
diagrs., tabs. (NACA RM A54A04) 



TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF BODY INDENTATION FOR 
BOATTAIL AND CYLINDRICAL AFTERBODY 
SHAPES ON THE AERODYNAMIC CHARACTERIS- 
TICS OF AN UNSWEPT-WING-BODY COMBINA- 
TION. Thomas C. Kelly. March 1954. 22p. 
diagrs., tab. (NACA RM L54A08) 



TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF TAPER RATIO, BODY INDEN- 
TATION, FIXED TRANSITION, AND AFTERBODY 
SHAPE ON THE AERODYNAMIC CHARACTERIS- 
TICS OF A 45° SWEPTBACK WING-BODY COMBI- 
NATION. Francis G. Morgan, Jr., and Melvin M. 
Carmel. March 1954. 37p. diagrs., tab. 
(NACA RM L54A15) 



AERODYNAMIC CHARACTERISTICS AT TRANSONIC 
AND SUPERSONIC SPEEDS OF A ROCKET- 
PROPELLED AIRPLANE CONFIGURATION HAVING 
A 52.50 DELTA WING AND A LOW, SWEPT HORI- 
ZONTAL TAIL. Alan B. Kehlet. March 1954. 31p. 
diagrs., photos. (NACA RM L54A20) 



THE EFFECT OF A CHANGE IN BODY SHAPE ON 
THE LOADING OF A 45° SWEPTBACK WING-BODY 
COMBINATION AT TRANSONIC SPEEDS. Donald L. 

Loving. April 1954. 67p. diagrs., photo. 
(NACA RM L54B09) 



INVESTIGATION AT HIGH SUBSONIC SPEEDS OF 
FINNED AND UNFINNED BODIES MOUNTED AT 
VARIOUS LOCATIONS FROM THE WINGS OF UN- 
SWEPT, AND SWEPT-WING-FUSELAGE MODELS, 
INCLUDING MEASUREMENTS OF BODY LOADS. 
William J. Alford, Jr., and H. Norman Silvers. 
April 1954. 93p. diagrs,, photos., tabs. 
(NACA RM L54B1S) 



INVESTIGATION AT HIGH SUBSONIC SPEEDS OF 
THE EFFECT OF ADDING VARIOUS COMBINATIONS 
OF MISSILES ON THE AERODYNAMIC CHARACTER- 
ISTICS OF SWEPTBACK AND UNSWEPT WINGS 
COMBINED WITH A FUSELAGE. H. Norman 
Silvers and WiUiam J. Alford, Jr. June 1954. 39p. 
diagrs., photo., tabs. (NACA RM L54D20) 



LOW-AMPLITUDE DAMPING-IN-PITCH CHARAC- 
TERISTICS OF TAILLESS DELTA-WING-BODY 
COMBINATIONS AT MACH NUMBERS FROM 0.80 
TO 1.35 AS OBTAINED WITH ROCKET-POWERED 
MODELS. Charles T. D'Aiutolo. June 1954. 34p. 
diagrs., photos., tab. (NACA RM L54D29) 



THE EFFECT OF CANOPY LOCATION ON THE 
AERODYNAMIC CHARACTERISTICS OF A SWEPT- 
BACK WING -BODY CONFIGURATION AT TRAN- 
SONIC SPEEDS. Harold L. Robinson. June 1954. 
14p. diagrs., photo. (NACA RM L54E11) 



A FLIGHT INVESTIGATION AT TRANSONIC SPEEDS 
OF THE AERODYNAMIC CHARACTERISTICS OF A 
MODEL HAVING A THIN UNSWEPT WING OF 
ASPECT RATIO 3.1. Maurice D. White. August 
1954. 41p. diagrs., photo., tabs. 
(NACA RM A54E12) 



AN EXPERIMENTAL INVESTIGATION OF REDUC- 
TION IN TRANSONIC DRAG RISE AT ZERO LIFT BY 
THE ADDITION OF VOLUME TO THE FUSELAGE 
OF A WING-BODY-TAIL CONFIGURATION AND A 
COMPARISON WITH THEORY. George H. Holdaway. 
August 1954. 35p. diagrs., photos., tabs. 
(NACARM A54F22) 



62 



(1) AERODYNAMICS 



LIFT AND DRAG CHARACTERISTICS OF THE 
DOUGLAS D-558-II RESEARCH AIRPLANE OB- 
TAINED IN EXPLORATORY FLIGHTS TO A MACH 
NUMBEROF2.0. Jack Nugent. August 1954. 20p. 
diagrs., photo., tab. (NACA RM L54F03) 



INVESTIGATION OF THE EFFECT OF INDENTATION 
ON AN M-PLAN-FORM-WING-BODY COMBINATION 
AT TRANSONIC SPEEDS. Donald L. Loving. 
August 1954. 24p. diagrs., photos., tab. 
(NACA RM L54F14) 



EFFECTS OF OVERHANG BALANCE ON THE 
HINGE-MOMENT AND EFFECTIVENESS CHARAC- 
TERISTICS OF AN UNSWEPT TRAILING-EDGE 
CONTROL ON A 60° DELTA WING AT TRANSONIC 
AND SUPERSONIC SPEEDS. Lawrence D. Guy. 
September 1954. 48p. diagrs., photo. 
(NACA RM L54G12a) 



SOME EFFECTS OF AILERON SPAN, AILERON 
CHORD, AND WING TWIST ON ROLLING EFFEC- 
TIVENESS AS DETERMINED BY ROCKET- 
POWERED MODEL TESTS AND THEORETICAL 
ESTIMATES. H. Kurt Strass and Warren A. Tucker. 
September 1954. 29p. diagrs., photos., tabs. 
(NACA RM L54G13) 



AERODYNAMIC CHARACTERISTICS AT TRANSONIC 
AND SUPERSONIC SPEEDS OF A ROCKET- 
PROPELLED AIRPLANE CONFIGURATION HAVING 
A DIAMOND -PLAN -FORM WING OF ASPECT RATIO 
3.08 AND A LOW, SWEPT HORIZONTAL TAIL. 
Alan B. Kehlet. September 1954. 37p. diagrs., 
photos. (NACA RM L54G27a) 



WING PRESSURE DISTRIBUTIONS AT LOW LIFT 
FOR THE XF-92A DELTA-WING AIRPLANE AT 
TRANSONIC SPEEDS. Earl R. Keener. October 
1954. 54p. diagrs., photos., tabs. 
(NACA RM H54H06) 



LONGITUDINAL STABILITY CHARACTERISTICS IN 
ACCELERATED MANEUVERS AT SUBSONIC AND 
TRANSONIC SPEEDS OF THE DOUGLAS D-558-II 
RESEARCH AIRPLANE EQUIPPED WITH A 
LEADING-EDGE WING CHORD-EXTENSION. Jack 
Fischel and Cyril D. Brunn. October 1954. 62p. 
diagrs., photos , tab. (NACA RM H54H16) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR-ARC SECTIONS AND 40° SWEEPBACK. 
STATIC LONGITUDINAL AND LATERAL STABILITY 
AND CONTROL CHARACTERISTICS AT A MACH 
NUMBER OF 1.89. M. Leroy Spearman and Edward 
B. Palazzo. October 1954. 24p. diagrs., photo., 
tab. (NACA RM L54G26a) 



FREE -FLIGHT MEASUREMENTS OF THE ROLLING 
EFFECTIVENESS AND OPERATING CHARACTER- 
ISTICS OF A BELLOWS-ACTUATED SPLIT-FLAP 
AILERON ON A 60<> DELTA WING AT MACH NUM- 
BERS BETWEEN 0.8 AND 1.8. Eugene D. Schult. 
October 1954. 33p. diagrs., photos. 
(NACA RM L54H17) 



AN INVESTIGATION OF THE EFFECTS OF A GEO- 
METRIC TWIST ON THE AERODYNAMIC LOADING 
CHARACTERISTICS OF A 450 SWEPTBACK WING- 
BODY CONFIGURATION AT TRANSONIC SPEEDS. 
Claude V. Williams. October 1954. 87p. diagrs., 
photos., tabs. (NACA RM L54H18) 



DETERMINATION OF LONGITUDINAL HANDLING 
QUALITIES OF THE D-558-II RESEARCH AIRPLANE 
AT TRANSONIC AND SUPERSONIC SPEEDS TO A 
MACH NUMBER OF ABOUT 2.0. Herman O. 
Ankenbruck. November 1954. 25p. diagrs., photos., 
tab. (NACA RM H54G29a) 



A FLIGHT INVESTIGATION OF THE TRANSONIC 
AREA RULE FOR A 52.5° SWEPTBACK WING-BODY 
CONFIGURATION AT MACH NUMBERS BETWEEN 
0.8 AND 1.6. Sherwood Hoffman. November 1954. 
25p. diagrs., photos., tab. (NACA RM L54H13a) 



LONGITUDINAL STABILITY CHARACTERISTICS AT 
TRANSONIC SPEEDS OF A CANARD CONFIGURA- 
TION HAVING A 45° SWEPTBACK WING OF ASPECT 
RATIO 6.0 AND NACA 65A009 AIRFOIL SECTION. 
A. James Vitale and John C McFall, Jr. November 
1954. 24p. diagrs., photos., tab. 
(NACA RM L54I01) 



LOW-AMPLITUDE DAMPING-IN-PITCH CHARAC- 
TERISTICS OF FOUR TAILLESS SWEPT WING- 
BODY COMBINATIONS AT MACH NUMBERS FROM 
0.85 TO 1.30 AS OBTAINED WITH ROCKET- 
POWERED MODELS. Charles T. D'Aiutolo. 
November 1954. 34p. diagrs., photos., tab. 
(NACA RM L54I10) 



A FLIGHT INVESTIGATION AT TRANSONIC 
SPEEDS AND SMALL ANGLES OF ATTACK OF THE 
AERODYNAMIC CHARACTERISTICS OF A MODEL 
HAVING A 450 SWEPTBACK WING OF ASPECT 
RATIO 3 WITH AN NACA 64A006 AIRFOIL SECTION. 
George H. Holdaway. January 1955. 32p. diagrs., 
photo., tab. (NACA RM A54I17) 



EFFECT OF TAPER RATIO ON LIFT, DRAG, AND 
PITCHING -MOMENT CHARACTERISTICS OF THIN 
WINGS OF ASPECT RATIO 3 WITH 53.1° SWEEP- 
BACK OF LEADING EDGE AT SUBSONIC AND 
SUPERSONIC SPEEDS. Benton E. Wetzel. 
January 1955. 25p. diagrs., photo., tabs. 
(NACA RM A54J20) 



LONGITUDINAL STABILITY CHARACTERISTICS 
AT MACH NUMBERS UP TO 0.92 OF A WING- 
BODY-TAIL COMBINATION HAVING A WING WITH 
45° OF SWEEPBACK AND A TAIL IN VARIOUS 
VERTICAL POSITIONS. Jack D. Stephenson, 
Angelo Bandettini, and Ralph Selan. January 1955. 
64p. diagrs., photos., tabs. (NACA RM A54K09) 



ROLLING PERFORMANCE OF THE REPUBLIC 
YF-84F AIRPLANE AS MEASURED IN FLIGHT. 
JohnB. McKay. January 1955. 24p. diagrs., 
photo., tab. (NACA RM H54G20a) 



EFFECTS OF BODY INDENTATION ON THE DRAG 
CHARACTERISTICS OF A DELTA-WING-BODY 
COMBINATION AT TRANSONIC SPEEDS . Dewey E . 
Wornom and Robert S. Osborne. January 1955. 
32p. diagrs., photos., tabs. (NACA RM L54K12a) 



EFFECTS OF INCREASING REYNOLDS NUMBER 
FROM 2 x 106 TO 6 x 10$ ON THE AERODYNAMIC 
CHARACTERISTICS AT TRANSONIC SPEEDS OF A 
450 SWEPT WING WITH 6° LEADING-EDGE DROOP. 
James W. SchmeerandJ. Lawrence Cooper 
February 1955. 22p. diagrs., photo. 
(NACA RM L54L10) 



( 1 ) AERODYNAMICS 



63 



INVESTIGATION OF THE LATERAL STABILITY 
CHARACTERISTICS OF THE DOUGLAS X-3 CON- 
FIGURATION AT MACH NUMBERS FROM 0.6 TO 
11 BY MEANS OF A ROCKET-PROPELLED 
MODEL. Jesse L. Mitchell and Robert F. Peck. 
February 1955. 37p. diagrs., photo., tabs. 
(NACA RM L54L20) 



EFFECTS OF TAPER RATIO ON THE LONGITUDI- 
NAL CHARACTERISTICS AT MACH NUMBERS 
FROM 0.6 TO 1.4 OF A WING-BODY-TAIL COMBI- 
NATION HAVING AN UNSWEPT WING OF ASPECT 
RATIO 3. James L. Summers, Stuart L. Treon, 
and Lawrence A. Graham. March 1955. 45p. 
diagrs., photo. (NACA RM A54L20) 



A FLIGHT INVESTIGATION AT TRANSONIC SPEEDS 
OF A MODEL HAVING A TRIANGULAR WING OF 
ASPECT RATIO 4. Loren G. Bright. March 1955. 
40p. diagrs., photos., tabs. (NACA RM A54L27) 



EFFECTS OF SWEEP AND TAPER RATIO ON THE 
LONGITUDINAL CHARACTERISTICS OF AN ASPECT 
RATIO 3 WING-BODY COMBINATION AT MACH 
NUMBERS FROM 0.6 TO 1.4. Earl D. Knechtel and 
James L. Summers. March 1955. 36p. diagrs., 
photo. (NACA RM A55A03) 



WING-LOAD MEASUREMENTS AT SUPERSONIC 
SPEEDS OF THE DOUGLAS D-558-II RESEARCH 
AIRPLANE. Glenn H. Robinson, George E. Cothren, 
Jr., and Chris Pembo. March 1955. 20p. diagrs., 
photos., tab. {NACA RM H54L27) 



THE ROLLING MOMENT DUE TO SIDESLD? OF 
SWEPT WINGS AT SUBSONIC AND TRANSONIC 
SPEEDS. Edward C Polhamus and William C . 
S lee man, Jr. March 1955. 81p. diagrs., photos., 
tabs. (NACA RM L54L01) 



FREE -FLIGHT INVESTIGATION TO DETERMINE 
SOME EFFECTS OF TAIL DAMPING AND WING- 
TAIL INTERFERENCE ON THE ROLLING EFFEC- 
TIVENESS OF INBOARD AND OUTBOARD AILERONS 
ON AN UNTAPERED SWEPTBACK WING. Roland D. 
English. March 1955. 18p. diagrs., photos. 
(NACA RM L54L17a) 



AN EXPERIMENTAL INVESTIGATION OF TWO 
METHODS FOR REDUCING TRANSONIC DRAG OF 
SWEPT-WING AND BODY COMBINATIONS. John B. 
McDevitt. April 1955. 27p. diagrs., photos. 
(NACA RM A55B21) 



TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF TAPER RATIO AND BODY IN- 
DENTATION ON THE AERODYNAMIC LOADING 
CHARACTERISTICS OF A 45° SWEPTBACK WING 
IN THE PRESENCE OF A BODY. James B. Delano 
andJohnP. Mugler, Jr. April 1955. 53p. diagrs., 
photos., tab, (NACA RM L54L28) 



TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF SWEEPBACK AND THICKNESS 
RATIO ON THE WING LOADS OF A WING-BODY 
COMBINATION OF ASPECT RATIO 4 AND TAPER 
RATIO 0.6. Robert J. Piatt, Jr., and Joseph D. 
Brooks. April 1955. 44p. diagrs., photos., tab. 
(NACA RM L54L31b) 



A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE LONGITUDINAL FORCE AND MOMENT CHAR- 
ACTERISTICS OF TWO DELTA WINGS AND ONE 
CLIPPED-TIP DELTA WING OF 4 PERCENT 
THICKNESS ON A SLENDER BODY . William E . 
Palmer and Dale L. Burrows. April 1955. 31p. 
diagrs., photo. (NACA RM L55A07a) 



LATERAL STABILITY CHARACTERISTICS AT LOW 
LIFT BETWEEN MACH NUMBERS OF 0.85 AND 1.15 
OF A ROCKET-PROPELLED MODEL OF A SUPER- 
SONIC AIRPLANE CONFIGURATION HAVING A 
TAPERED WING WITH CIRCULAR-ARC SECTIONS 
AND 40« SWEEPBACK. Charles T. D'Aiutolo and 
Allen B. Hunuing. April 1955. 50p. diagrs., 
photos., tabs. (NACA RM L55A31) 



EFFECTS OF A DETACHED TAB ON THE HINGE- 
MOMENT AND EFFECTIVENESS CHARACTER- 
ISTICS OF AN UNSWEPT TRATLING-EDGE CON- 
TROL ON A 60° DELTA WING AT MACH NUMBERS 
FROM 0.75 TO 1.96. Odell A. Morris and 
Gertrude C. Westrick. April 1955. 38p. diagrs., 
photo. (NACA RM L55B15) 



EFFECT OF A WING LEADING-EDGE FLAP AND 
CHORD-EXTENSION ON THE HIGH SUBSONIC 
CONTROL CHARACTERISTICS OF AN AILERON 
LOCATED AT TWO SPANWISE POSITIONS . Robert 
F. Thompson and Robert T. Taylor. May 1955. 
59p. diagrs., photo., tabs. (NACA RM L55B18a) 



INVESTIGATION OF THE EFFECTS OF AN AIRFOIL 
SECTION MODIFICATION ON THE AERODYNAMIC 
CHARACTERISTICS AT SUBSONIC AND SUPERSONIC 
SPEEDS OF A THIN SWEPT WING OF ASPECT 
RATIO 3 IN COMBINATION WITH A BODY. David 
Graham and William T, Evans. June 1955. 46p. 
diagrs., tabs. (NACA RM A55D11) 



A COMPARISON AT MACH NUMBERS UP TO 0.92 
OF THE CALCULATED AND EXPERIMENTAL 
DOWNWASH AND WAKE CHARACTERISTICS AT 
VARIOUS HORIZONTAL TAIL HEIGHTS BEHIND A 
WING WITH 45° OF SWEEPBACK. Jack D. . 
Stephenson, Ralph Selan, and Angelo Bandettini. 
June 1955. 81p. diagrs., photos., tabs. 
(NACA RM A55D27a) 



EXPERIMENTAL FLUTTER RESULTS FOR 
CANTILEVER-WING MODELS AT MACH NUMBERS 
UP TO 3.0. W. J. Tuovila and John Locke McCarty. 
June 1955. 13p. diagrs., tab. (NACA RM L55E11) 



STABILITY AND CONTROL CHARACTERISTICS 
OBTAINED DURING DEMONSTRATION OF THE 
DOUGLAS X-3 RESEARCH AIRPLANE. Richard E. 
Day and Jack Fischel. July 1955. 51p. diagrs., 
photos., tab. (NACA RM H55E16) 



ADDITIONAL COMPARISONS BETWEEN COMPUTED 
AND MEASURED TRANSONIC DRAG-RISE COEFFI- 
CIENTS AT ZERO LIFT FOR WRJG-BODY-TAIL 
CONFIGURATIONS. George H. Holdaway. August 
1955. 43p. diagrs., photo., tabs. 
(NACA RM A55F06) 



A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE STATIC LONGITUDINAL CHARACTERISTICS 
OF A 3-PERCENT-THICK, ASPECT-RATIO-3, 
DELTA WING CAMBERED AND TWISTED FOR HIGH 

LIFT-DRAG RATIOS. Dale L. Burrows and Warren 
A. Tucker. August 1955. 38p. diagrs., photos., 
tab. (NACA RM L55F02a) 



64 



(1) AERODYNAMICS 



A FLIGHT INVESTIGATION AT TRANSONIC SPEEDS 
OF A MODEL HAVING A TRIANGULAR WING OF 
ASPECT RATIO 2. Maurice D. White. September 
1955. 39p. diagrs., photo., tabs. 
(NACA RM A55F21) 



COLLECTION AND SUMMARY OF FLAP -TYPE- 
AILERON ROLLING-EFFECTIVENESS DATA AT 
ZERO LIFT AS DETERMINED BY ROCKET- 
POWERED MODEL TESTS AT MACH NUMBERS 
BETWEEN 0.3 AND 1.6. H. Kurt Strass, Emily W. 
Stephens, E. M. Fields, and Eugene D. Schult. 
September 1955. 95p. diagrs., photos., tabs. 
(NACA KM L55* 14) 



LONGITUDINAL CHARACTERISTICS AT TRANSONIC 
AND SUPERSONIC SPEEDS OF A ROCKET- 
PROPELLED AIRPLANE MODEL HAVING A 60° 
DELTA WING AND A LOW SWEPT HORIZONTAL 
TAIL. RobertF. Peck and Lucille C. Coltrane. 
September 1955. 33p. diagrs., photo., tabs. 
(NACA RM L55F27) 



TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE AERODYNAMIC LOADING CHARACTERISTICS 
OF A 60° DELTA WING IN THE PRESENCE OF A 
BODY WITH AND WITHOUT INDENTATION. John 
P. Mugler, Jr. September 1955. 30p. diagrs., 
photos., tab. {NACA RM L55G11) 



FREE-FLIGHT INVESTIGATION TO OBTAIN DRAG- 
AT-LIFT AND STABILITY DATA FOR A 60° DELTA- 
WING-BODY CONFIGURATION OVER A MACH NUM- 
BER RANGE OF 1 .3 TO 1 .6. Clement J . Welsh. 
October 1955. 23p. diagrs., photo., tab. 
(NACA RM L55G14) 



EFFECTS OF LEADING-EDGE RADIUS ON THE 
LONGITUDINAL STABILITY OF TWO 45° SWEPT - 
BACK WINGS INCORPORATING LEADING-EDGE 
CAMBER AS INFLUENCED BY REYNOLDS NUM- 
BERS UP TO 8.00 x 10 6 AND MACH NUMBERS UP 
TO 0.290. Gerald V. Foster. October 1955. 44p. 
diagrs. (NACA RM L55H04) 



A STUDY OF CONICAL CAMBER FOR TRIANGULAR 
AND SWEPTBACK WINGS. John W. Boyd, Eugene 
Migotsky, and Benton E. Wetzel. November 1955. 
79p. diagrs., tabs. (NACA RM A55G19) 



EFFECT OF LEADING-EDGE SWEEPBACK ON LIFT, 
DRAG, AND PITCHING-MOMENT CHARACTERIS- 
TICS OF THIN WINGS OF ASPECT RATIO 3 AND 
TAPER RATIO 0.4 AT SUBSONIC AND SUPERSONIC 
SPEEDS. Benton E. Wetzel. November 1955. 22p. 
diagrs., tabs. (NACA RM A55H04a) 



AERODYNAMIC LOADS ON AN EXTERNAL STORE 
ADJACENT TO A 45° SWEPTBACK WING AT MACH 
NUMBERS FROM 0.70 TO 1.96, INCLUDING AN 
EVALUATION OF TECHNIQUES USED. Lawrence 
D. Guy and William M. Hadaway. November 1955. 
109p. diagrs., photo., tab. (NACA RM L55H12) 



WIND-TUNNEL INVESTIGATION AT TRANSONIC 
SPEEDS OF A JET CONTROL ON AN 80° DELTA- 
WING MISSILE. Thomas R. Turner and Raymond D. 
Vogler. November 1955. 32p. diagrs. 
(NACA RM L55H22) 



THE EFFECT OF LEADING-EDGE DROOP UPON 
THE PRESSURE DISTRIBUTION AND AERODYNAM- 
IC LOADING CHARACTERISTICS OF A 45° SWEPT- 
BACK WING AT TRANSONIC SPEEDS. Janies W. 
Schmeer. November 1955. 42p. diagrs., photos. 
(NACA RM L 5 511 6) 



INVESTIGATION AT HIGH SUBSONIC SPEEDS OF 
THE STATIC LONGITUDINAL STABILITY CHARAC- 
TERISTICS OF A MODEL HAVING CROPPED-DELTA 
AND UNSWEPT WING PLAN FORMS AND SEVERAL 
TAIL CONFIGURATIONS. Albert G. Few, Jr. 
November 1955. 107p. diagrs., photo., tab. 
(NACA km Lbt>I23a) 



TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF INCIDENCE AND BODY INDEN- 
TATION ON THE WING LOADS OF A 45° SWEPT- 
BACK WING-BODY COMBINATION. Robert J. 
Piatt, Jr. January 1956. 24p. diagrs., photos., 
tab. (NACA RM L55H26) 



AERODYNAMICS OF BODIES, WINGS, AND WING- 
BODY COMBINATIONS AT HIGH ANGLES OF AT- 
TACK AND SUPERSONIC SPEEDS. Jack N. 
Nielsen, J. Richard Spahr, and Frank Centolanzi. 
February 1956. 12p. diagrs. (NACA RM A55Ll3c) 



AN INVESTIGATION OF THE AERODYNAMIC CHAR- 
ACTERISTICS AT TRANSONIC MACH NUMBERS OF 
A SWEPT -WING SUPERSONIC BOMBER CONFIGU- 
RATION. Ralph P. Bielat and J. Lawrence Cooper. 
February 1956. 92p. diagrs., photos., tabs. 
(NACA RM L53F05) 



SOME EFFECTS OF SWEEP AND THICKNESS ON 
THE EXPERIMENTAL DOWNWASH CHARACTER- 
ISTICS AT TRANSONIC SPEEDS OF A SERIES OF 
HIGHLY TAPERED WINGS WITH AN ASPECT RATIO 
OF 3. TRANSONIC -BUMP METHOD. Albert G. 
Few, Jr. February 1956. 65p. diagrs., photo. 
(NACARM L55J12) 



PRELIMINARY FREE-FLIGHT STUDY OF THE 
DRAG AND STABILITY OF A SERIES OF SHORT - 
SPAN MISSILES AT MACH NUMBERS FROM 0.9 TO 
1.3. James Rudyard Hall. February 1956. 14p. 
diagrs., photo. (NACARM L55J13) 



TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE AERODYNAMIC LOADING CHARACTERISTICS 
OF A HIGHLY TAPERED UNSWEPT WING IN THE 
PRESENCE OF A BODY WITH AND WITHOUT IN- 
DENTATION. Joseph D. Brooks. February 1956. 
30p. diagrs., photos., tab. (NACARM L55J20) 



WIND-TUNNEL INVESTIGATION AT HIGH SUBSONIC 
SPEEDS OF SOME EFFECTS OF FUSELAGE CROSS- 
SECTION SHAPE AND WING HEIGHT ON THE STAT- 
IC LONGITUDINAL AND LATERAL STABILITY 
CHARACTERISTICS OF A MODEL HAVING A 45° 
SWEPT WING. Thomas J. King, Jr. February 
1956. 61p. diagrs., photo. (NACA RM L55J25) 



WIND-TUNNEL INVESTIGATION AT TRANSONIC 
SPEEDS OF A JET CONTROL ON A 35° SWEPT 
WING. TRANSONIC -BUMP METHOD. Raymond D. 
Vogler and Thomas R. Turner. February 1956. 
17p. diagrs. (NACA RM L55K09) 



65 



(1) AERODYNAMICS 



EXPERIMENTAL INVESTIGATION AT HIGH SUB- 
SONIC SPEED OF THE ROLLING STABILITY 
DERIVATIVES OF A COMPLETE MODEL HAVING 
A CLIFFED-DELTA WING AND A HIGH HORIZON- 
TAL TAIL. William C. Sieeman, Jr., and Albert G. 
Few, Jr. February 1956. 32p. diagrs., tab. 
(NACARM L55K11) 



LONGITUDINAL STABILITY INVESTIGATION FOR 
A MACH NUMBER RANGE OF 0.8 TO 1.7 OF AN 
AIRPLANE CONFIGURATION WITH A 45° SWEPT 
WING AND A LOW HORIZONTAL TAIL- John C. 
McFall, Jr. February 1956. 32p. diagrs., photos., 
tab. (NACA RM L55L09) 



RESULTS OF ROCKET MODEL TEST OF AN AIR- 
PLANE CONFIGURATION HAVING AN ARROW WING 
AND SLENDER FLAT -SIDED FUSELAGE. LIFT, 
DRAG, LONGITUDINAL STABILITY, LATERAL 
FORCE, AND JET EFFECTS AT MACH NUMBERS 
BETWEEN 1.0 AND 2.3. Robert F. Peck. 
February 1956. 26p. diagrs., photo. 
(NACARM L55L29) 



EFFECTS OF LEADING-EDGE RADIUS ON THE 
LONGITUDINAL STABILITY CHARACTERISTICS OF 
TWO 60° SWEPTBACK WINGS AT HIGH REYNOLDS 
NUMBERS. William C Schneider. March 1956. 
46p. diagrs. (NACA RM L55L30) 



EXPERIMENTAL RESULTS FROM A TEST IN 
ROUGH AIR AT HIGH SUBSONIC SPEEDS OF A 
TAILLESS ROCKET MODEL HAVING CRUCIFORM 
TRIANGULAR WINGS, AND A NOTE ON THE CAL- 
CULATION OF MEAN SQUARE LOADS OF AIR- 
CRAFT IN CONTINUOUS ROUGH AIR. A. James 
Vitale and Jesse L. Mitchell. April 1956. 25p. 
diagrs., photo., tab. (NACARM L55L28) 



AN EXPERIMENTAL STUDY AT HIGH SUBSONIC 
SPEEDS OF SEVERAL TAIL CONFIGURATIONS ON 
A MODEL WITH AN UNSWEPT WING. William C. 
Sieeman, Jr. April 1956. 67p. diagrs., photos. 
(NACA RM L56A06a) 



LATERAL STABILITY CHARACTERISTICS BE- 
TWEEN MACH NUMBERS OF 0.80 AND 1-57 AND 
SIMULATION OF COUPLED MOTION AT MACH 
NUMBER 1.30 OF A ROCKET-PROPELLED MODEL 
OF AN AIRPLANE CONFIGURATION HAVING THIN 
HIGHLY TAPERED 45° SWEPTBACK SURFACES. 
Charles T. D'Aiutolo and Allen B. Henning. April 
1956. 41p. diagrs., photos., tabs. 
(NACARM L56A17) 



INVESTIGATION AT HIGH SUBSONIC SPEEDS OF 
THE EFFECT OF HORIZONTAL -TAIL LOCATION 
ON LONGITUDINAL AND LATERAL STABILITY 
CHARACTERISTICS OF A COMPLETE MODEL 
HAVING A SWEPTBACK WING IN A HIGH LOCA- 
TION. H. Norman Silvers and Thomas J. King, Jr. 
April 1956. 46p. diagrs., tab. (NACA RM L56B10) 



EFFECTS OF REYNOLDS NUMBER AND LEADING- 
EDGE SHAPE ON THE LOW -SPEED LONGITUDINAL 
STABILITY OF A 6-PERCENT-THICK 45° SWEPT- 
BACK WING. William C. Schneider. April 1956. 
32p. diagrs. (NACA RM L56B14) 



AERODYNAMIC DAMPING AT MACH NUMBERS OF 
i .3 AND 1 .6 OF A CONTROL SURFACE ON A TWO- 
DIMENSIONAL WING BY THE FREE -OSCILLATION 
METHOD. W. J. Tuovila and Robert W. Hess. 
May 1956. 21p. diagrs., tabs. (NACA RM L56A26a) 



EFFECT OF WING CAMBER AND TWIST AT MACH 
NUMBERS FROM 1.4 TO 2.1 ON THE LIFT, DRAG, 
AND LONGITUDINAL STABILITY OF A ROCKET- 
POWERED MODEL HAVING A 52-5° SWEPTBACK 
WING OF ASPECT RATIO 3 AND INLINE TAIL SUR- 
FACES. Warren Gillespie, Jr. May 1956. 29p. 
diagrs., photos., tabs. (NACA RM L56C16) 



EFFECT OF SEVERAL WING MODIFICATIONS ON 
THE SUBSONIC AND TRANSONIC LONGITUDINAL 
HANDLING QUALITIES OF THE DOUGLAS D-558-H 
RESEARCH AIRPLANE. Jack Fischel and Donald 
Reisert. June 1956. 57p. diagrs., photos., tabs. 
(NACA RM H56C30) 



THE EFFECT OF CONICAL CAMBER ON THE 
STATIC LONGITUDINAL, LATERAL, AND DIREC- 
TIONAL CHARACTERISTICS OF A 45° SWEPTBACK 
WING AT MACH NUMBERS UP TO 0.96. Robert I. 
Sammonds and Robert M. Reynolds. July 1956. 
64p. diagrs., tabs. (NACA RM A56D02) 



EFFECT OF WING SIZE AND AMOUNT OF INDEN- 
TATION ON APPLICABILITY OF TRANSONIC AREA 
RULE TO SWEPT -WING CONFIGURATIONS. 
James Rudyard Hall. July 1956. 33p. diagrs., 
photos., tabs. (NACA RM L55F03) 



RESULTS FROM AN INVESTIGATION IN ROUGH 
AIR AT MACH NUMBERS FROM 0.84 TO 1.67 OF A 
TAILLESS ROCKET MODEL HAVING 60° TRIANGU- 
LAR WINGS. A. James Vitale. July 1956. I6p. 
diagrs., photo., tab. (NACA RM L56F07a) 



THE VARIATION WITH WING ASPECT RATIO OF 
FLAP EFFECTIVENESS ON THIN RECTANGULAR 
WINGS AT TRANSONIC SPEEDS. John G. Lowry 
and Robert T. Taylor. August 1956. 6 Op. diagrs., 
tabs. (NACA RM L56E18) 



WIND-TUNNEL INVESTIGATION OF THE EFFECTS 
OF WING THICKNESS ON THE STATIC LONGITU- 
DINAL AND LATERAL STABILITY OF UNSWEPT 
WINGS OF ASPECT RATIO 3 AT HIGH SUBSONIC 
SPEEDS. William C. Hayes, Jr., and Edward C. 
Polhamus. August 1956. 43p. diagrs., photos. 
(NACA RM L56E30a) 



HINGE MOMENT AND EFFECTIVENESS OF AN 
UNSWEPT CONSTANT-CHORD CONTROL AND AN 
OVERHANG-BALANCED, SWEPT HINGE -LINE 
CONTROL ON AN 80° SWEPT POINTED WING AT 
MACH NUMBERS FROM 0.75 TO 1.96. Lawrence D. 
Guy. August 1956. 39p. diagrs., photo. 
(NACA RM L56F11) 



WIND-TUNNEL INVESTIGATION OF DAMPING IN 
ROLL AT SUPERSONIC SPEEDS OF TRIANGULAR 
WINGS AT ANGLES OF ATTACK. Russell W 
McDearmon and Robert A. Jones. September 1956. 
32p. diagrs., photos., tab. (NACA RM L56F13a) 



INVESTIGATION OF SPOILER-SLOT-DEFLECTOR 
AILERONS AND OTHER SPOILER AILERONS ON A 
45° SWEPTBACK -WING- FUSELAGE COMBINATION 
AT MACH NUMBERS FROM 0.60 TO 1.03. F. E. 
West, Jr., Charles F. Whitcomb, and James W. 
Schm'eer. September 1956. 59p. diagrs., tab. 
(NACA RM L56F15) 



6b 



(1) AERODYNAMICS 



TRANSONIC WIND-TUNNEL INVESTIGATION OF 
STATIC LONGITUDINAL FORCE AND MOMENT 
CHARACTERISTICS OF TWO WING-BODY COMBI- 
NATIONS WITH CLIPPED-TIP AND FULL DELTA 
WINGS OF ASPECT RATIO 1.73. Dale L. Burrows. 
September 1956. 26p. diagrs. (NACA RM L56F21) 



FREE-FLIGHT INVESTIGATION OVER A MACH 
NUMBER RANGE FROM 0.74 TO 1.43 AT LIFT CO- 
EFFICIENTS FROM -0.15 TO 0.75 OF AN AIRPLANE - 
CONFIGURATION MODEL HAVING A 52.5° DELTA 
WTNG ANH A TOW SWEPT HORIZONTAL TAIL. 
Alan B. Kehlet. September 1956. 41p. diagrs., 
photos. (NACA RM L56G09) 



WIND-TUNNEL MEASUREMENTS OF WTNG BUF- 
FETING ON 1/16-SCALE MODEL OF DOUGLAS 
D-558-H RESEARCH AIRPLANE. William B. Kemp, 
Jr., and Thomas J. King, Jr. September 1956. 
34p. diagrs., photos., tabs. (NACA RM L56G31) 



EXPERIMENTAL HINGE MOMENTS ON FREELY 
OSCILLATING FLAP -TYPE CONTROL SURFACES. 
C. William Martz. October 1956. 29p. diagrs., 
photos., tab. (NACA RM L56G20) 



STATIC STABILITY CHARACTERISTICS OF A 
CAMBERED-DELTA-WING MODEL AT HIGH 
SUBSONIC SPEEDS. William C. Moseley, Jr. 
October 1956. 35p. diagrs., photos. 
(NACA RM L56H13) 



COMBINED EFFECTS OF WING TAPER RATIO AND 
LOW HORIZONTAL -TAIL POSITION ON LONGITU- 
DINAL STABILITY OF A 45° SWEPTBACK WING- 
BODY COMBINATION AT TRANSONIC SPEEDS. 
Stanley H. Spooner. October 1956. 28p. diagrs. f 
tab. (NACA RM L56H24) 



WING LOADS AND LOAD DISTRIBUTIONS THROUGH- 
OUT THE LIFT RANGE OF THE DOUGLAS X- 3 
RESEARCH AIRPLANE AT TRANSONIC SPEEDS. 
Earl R. Keener and Gareth H. Jordan. November 
1956. 191p. diagrs., photo., tabs. 
(NACA RM H56G13) 



LIFT -CURVE SLOPES DETERMINED IN FLIGHT ON 
A FLEXIBLE SWEPT -WING JET BOMBER. William 
S. Aiken, Jr., and Raymond A. Fisher. December 
1956. 49p. diagrs., photos., tabs. 
(NACARM L56E21a) 



FORCE TEST RESULTS FOR BODY-MOUNTED 
LATERAL CONTROLS AND SPEED BRAKES ON A 
45° SWEPT-WING MODEL AT MACH NUMBERS 
FROM 0.80 TO 0.98. F. E. West, Jr., and Chris C. 
Critzos. December 1956. 32p. diagrs., photos., 
tab. (NACA RM L56I05) 



A SUMMARY AND ANALYSIS OF THE LOW -SPEED 
LONGITUDINAL CHARACTERISTICS OF SWEPT 
WINGS AT HIGH REYNOLDS NUMBER. G. Chester 
Furlong and James G. McHugh. 1957. iii, 14 9p. 
diagrs., tabs. (NACA Rept. 1339. Supersedes 
RM L52D16) 



WIND-TUNNEL INVESTIGATION OF THE AERODY- 
NAMIC CHARACTERISTICS OF A SERIES OF 
SWEPT, HIGHLY TAPERED, THIN WINGS AT 
TRANSONIC SPEEDS. TRANSONIC-BUMP METHOD. 
Albert G. Few, Jr., and Paul G. Fournier. January 
1957. 57p. diagrs., photo. (NACA RM L56I24) 



STATIC LONGITUDINAL CHARACTERISTICS AT 
HIGH SUBSONIC SPEEDS OF A COMPLETE AIR- 
PLANE MODEL WITH A HIGHLY TAPERED WING 
HAVING THE 0.80 CHORD LINE UNSWEPT AND 
WITH SEVERAL TAIL CONFIGURATIONS. Kenneth 
W. Goodson. January 1957. 57p. diagrs., photo., 
tabs. (NACA RM L56J03) 



THE SUBSONIC STATIC AERODYNAMIC CHARAC- 
TERISTICS OF AN AIRPLANE MODEL HAVING A 
TRIANGULAR WING OF ASPECT RATIO 3.1- EF- 
FECTS OF HORIZONTAL-TAIL LOCATION AND 
SIZE ON THE LONGITUDINAL CHARACTERISTICS. 
Bruce E. Tinling and Armando E. Lopez. July 1957. 
85p. diagrs., photo., tabs. (NACA TN 4041. Super- 
sedes RM A53L1 5) 



THE SUBSONIC STATIC AERODYNAMIC CHARAC- 
TERISTICS OF AN AIRPLANE MODEL HAVING A 
TRIANGULAR WING OF ASPECT RATIO 3. 
m - EFFECTS OF TRAILING-EDGE FLAPS. Bruce 
E. Tinling and A. V. Karpen. July 1957. 37p. 
diagrs., photos., tabs. (NACA TN 4043. Super- 
sedes RM A54L07) 



COMPRESSIBILITY EFFECTS ON A HOVERING 
HELICOPTER ROTOR HAVING AN NACA 0018 ROOT 
AIRFOIL TAPERING TO AN NACA 0012 TIP AIR- 
FOIL. Robert D. Powell, Jr. September 1957. 
25p. diagrs. (NACA RM L57F26) 



WIND-TUNNEL INVESTIGATION OF THE STATIC 
LATERAL STABILITY CHARACTERISTICS OF 
WING-FUSELAGE COMBINATIONS AT HIGH SUB- 
SONIC SPEEDS. TAPER-RATIO SERIES! James 
W. Wiggins and Paul G. Fournier. October 1957. 
25p. diagrs., photos. (NACA TN 4174. Supersedes 
RM L53B25a) 



FLIGHT DATA PERTINENT TO BUFFETING AND 
MAXIMUM NORMAL -FORCE COEFFICIENT OF THE 
DOUGLAS X-3 RESEARCH AIRPLANE. Thomas F. 
Baker, James A. Martin, and Betty J. Scott. 
November 1957. 41p. diagrs., photo., tabs. 
(NACA RM H57H09) 



INVESTIGATION OF DEFLECTORS AS GUST ALLE- 
VIATORS ON A 0.09-SCALE MODEL OF THE BELL 
X-5 AIRPLANE WITH VARIOUS WTNG SWEEP 
ANGLES FROM 20° TO 60^ AT MACH NUMBERS 
FROM 0.40 TO 0.90. Delwin R. Croom and Jarrett 
K. Huffman. November 1957. 28p. diagrs. 
(NACA TN 4175) 



FLIGHT INVESTIGATION OF THE TRANSONIC 
LONGITUDINAL AND LATERAL HANDLING QUALp 
ITIES OF THE DOUGLAS X-3 RESEARCH AIRPLANE. 
Jack Fischel, Euclid C. Holleman, and Robert A. 
Tremant. December 1957. 61p. diagrs., photos., 
tab. (NACA RM H 5 71 05) 



67 



(1) AERODYNAMICS 



ANALYSIS OF HORIZONTAL -TAIL LOADS IN 
PITCHING MANEUVERS, ON A FLEXIBLE SWEPT- 
WING JET BOMBER. William S. Aiken, Jr. 
December 1957. 58p. diagrs., photo., tabs. 
(NACA TN 4191) 



WIND-TUNNEL INVESTIGATION OF EFFECT OF 
SWEEP ON ROLLING DERIVATIVES AT ANGLES OF 
ATTACK UP TO 13° AND AT HIGH SUBSONIC MACH 
NUMBERS, INCLUDING A SEMIEMPIRICAL 
METHOD OF ESTIMATING THE ROLLING DERIVA- 
TIVES. James W. Wiggins. January 1958. 47p. 
diagrs., tab. (NACA TN 4185. Supersedes 
RM L54C26) 



EFFECTS OF FIXING BOUNDARY-LAYER TRANSI- 
TION FOR AN UNSWEPT-WING MODEL AND AN 
EVALUATION OF POROUS TUNNEL-WALL INTER- 
FERENCE FOR MACH NUMBERS FROM 0.60 TO 
1.40- Louis S. Stivers, Jr., and Garth W. Lippmann. 
April 1958. . 37p. diagrs. (NACA TN 4228) 



SOME MEASUREMENTS OF AERODYNAMIC 
FORCES AND MOMENTS AT SUBSONIC SPEEDS 
ON A RECTANGULAR WING OF ASPECT RATIO 2 
OSCILLATING ABOUT THE MIDCHORD. Edward 
Widmayer, Jr., Sherman A. Clevenson, and 
Sumner A. Leadbetter. May 1958. 45p. diagrs., 
tabs. (NACA TN 4240. Supersedes RM L53F19) 



EFFECTS OF FDCTNG TRANSITION ON THE TRAN- 
SONIC AERODYNAMIC CHARACTERISTICS OF A 
WING-BODY CONFIGURATION AT REYNOLDS NUM- 
BERS FROM 2.4 TO 12 MILLION. Lynn W. Hunton. 
July 1958. 56p. diagrs. (NACA TN 4279) 



WIND-TUNNEL INVESTIGATION OF THE HIGH- 
SUBSONIC STATIC LONGITUDINAL STABILITY 
CHARACTERISTICS OF SEVERAL WING-BODY CON- 
FIGURATIONS DESIGNED FOR HIGH LIFT -DRAG 
RATIOS AT A MACH NUMBER OF 1.4. Paul G. 
Fournier. July 1958. 42p. diagrs., photo., tab. 
(NACA TN 4340) 



LOW TU? MACH NUMBER STALL CHARACTERIS- 
TICS AND HIGH TIP MACH NUMBER COMPRESSI- 
BILITY EFFECTS ON A HELICOPTER ROTOR 
HAVING AN NACA 0009 TD? AIRFOIL SECTION. 
Robert D. Powell, Jr., and Paul J. Carpenter. July 
1958. 28p. diaers. (NACA TN 4355) 



THE STATIC LONGITUDINAL CHARACTERISTICS 
OF A TWISTED AND CAMBERED 45° SWEPTBACK 
WING AT MACH NUMBERS UP TO 0.96. Robert I. 
Sammonds and Robert M. Reynolds. August 1958. 
26p. diagrs., tab. (NACA RM A58C21) 



EXPLORATORY WIND-TUNNEL INVESTIGATION 
AT HIGH SUBSONIC AND TRANSONIC SPEEDS OF 
JET FLAPS ON UNSWEPT RECTANGULAR WINGS. 
Vernard E. Lockwood and Raymond D. Vogler 
August 1958. 37p. diagrs. (NACA TN 4353) 



THE EFFECTS OF AN INVERSE-TAPER LEADING- 
EDGE FLAP ON THE AERODYNAMIC CHARACTER- 
ISTICS IN PITCH OF A WING-BODY COMBINATION 
HAVING AN ASPECT RATIO OF 3 AND 45° OF 
SWEEPBACK AT MACH NUMBERS TO 0.92. Fred A. 
Demele and K. Harmon Powell. August 1958. 57p. 
diagrs., photo., tabs. (NACA TN 4366) 



INVESTIGATION OF MINIMUM DRAG AND MAXI- 
MUM LIFT-DRAG RATIOS OF SEVERAL WING-BODY 
COMBINATIONS INCLUDING A CAMBERED TRI- 
ANGULAR WING AT LOW REYNOLDS NUMBERS 
AND AT SUPERSONIC SPEEDS. Clinton E. Brown 
and L. K. Har grave. September 1958. 62p. diagrs., 
photos., tabs. (NACA TN 4020. Supersedes 
RM L51EU) 



EFFECTS OF COMPRESSIBILITY ON ROTOR HOV- 
ERING PERFORMANCE AND SYNTHESIZED BLADE- 
SECTION CHARACTERISTICS DERIVED FROM 
MEASURED ROTOR PERFORMANCE OF BLADES 
HAVING NACA 0015 AIRFOIL TD? SECTIONS. 
James P. Shivers and Paul J. Carpenter. September 
1958. 28p. diagrs. (NACA TN 4356) 



LIFT AND PROFILE -DRAG CHARACTERISTICS OF 
AN NACA 0012 AIRFOIL SECTION AS DERIVED 
FROM MEASURED HELICOPTER-ROTOR HOVER- 
ING PERFORMANCE. Paul J. Carpenter. 
September 1958. 28p. diagrs., photo. 
(NACA TN 4357) 



(i.2.2.7) 
WAKE 



AN INVESTIGATION OF A 0.16-SCALE MODEL OF 
THE DOUGLAS X-3 AIRPLANE TO DETERMINE 
MEANS OF IMPROVING THE LOW -SPEED LONGI- 
TUDINAL STABILITY AND CONTROL CHARACTER- 
ISTICS. John W. McKee and John M. Riebe. 
November 1952. 90p. diagrs., photos., tabs. 
(NACA RM L52H01) 



TOTAL-PRESSURE AND SCHLIEREN STUDffiS OF 
THE WAKES OF VARIOUS CANARD CONTROL SUR- 
FACES MOUNTED ON A MISSILE BODY AT A MACH 
NUMBER OF 1 .93. William B. Boatrlghf . 
November 1952. 47p. photos., diagrs. 
(NACA RM L 5 21 29) 



WIND-TUNNEL INVESTIGATION OF THE VORTEX 
WAKE AND DOWNWASH FIELD BEHIND TRIANGU- 
LAR WINGS AND WING-BODY COMBINATIONS AT 
SUPERSONIC SPEEDS. J. Richard Spahr and 
Robert R. Dickey. June 1953. 92p. diagrs., 
photos., tabs. (NACA RM A53D10) 



AN ANALYSIS OF PRESSURE STUDIES AND EX- 
PERIMENTAL AND THEORETICAL DOWNWASH 
AND SIDEWASH BEHIND FIVE POINTED-TIP WTOGS 
AT SUPERSONIC SPEEDS. William B. Boatright. 
April 1954. ii, 119p. diagrs., photos. 
(NACA RM L54B10) 



FREE-FLIGHT INVESTK5ATION TO DETERMINE 
SOME EFFECTS OF TAIL DAMPING AND WING- 
TAIL INTERFERENCE ON THE ROLLING EFFEC- 
TIVENESS OF INBOARD AND OUTBOARD AILERONS 
ON AN UNTAPERED SWEPTBACK WING. Roland p. 
English. March 1955. 18p. diagrs., photos. 
(NACA RM L54L17a) 



68 



(I) AERODYNAMICS 



A COMPARISON AT MACH NUMBERS UP TO 0.92 
OF THE CALCULATED AND EXPERIMENTAL 
DOWNWASH AND WAKE CHARACTERISTICS AT 
VARIOUS HORIZONTAL TAIL HEIGHTS BEHIND A 
WING WITH 450 OF SWEEPBACK. Jack D. 
Stephenson, Ralph Selan, and Angelo Bandettini. 
June 1955, 81p. diagrs., photos., tabs. 
(NACA RM A55D27a) 



SUMMARY AND ANALYSIS OF HORIZONTAL-TAIL 
CONTRIBUTION TO LONGITUDINAL STABILITY OF 
SWEPT -WING AIRPLANES AT LOW SPEEDS. 

ii, 133p. diagrs., tabs. (NACA RM L55E23a) ' 



AERODYNAMICS OF BODIES. WINGS, AND WING- 
BODY COMBINATIONS AT HIGH ANGLES OF AT- 
TACK AND SUPERSONIC SPEEDS. Jack N. 
Nielsen, J. Richard Spahr, and Frank Centolanzi. 
February 19SR 12p. diagrs. (NACA RM A55L13c) 



SOME EFFECTS OF SWEEP AND THICKNESS ON 
THE EXPERIMENTAL DOWNWASH CHARACTER- 
ISTICS AT TRANSONIC SPEEDS OF A SERIES OF 
HIGHLY TAPERED WINGS WITH AN ASPECT RATIO 
OF 3. TRANSONIC -BUMP METHOD. Albert G. 
Few, Jr. February 1956. 65p. diagrs., photo. 
(NACARM L55J12) 



FLIGHT MEASUREMENTS OF HORIZONTAL -TAIL 
LOADS ON THE DOUGLAS X-3 RESEARCH AIR- 
PLANE. Harriet J. Stephenson. April 1956. 33p. 
diagrs., photo., tab. (NACA RM H56A23) 



A THEORETICAL STUDY OF THE AERODYNAMICS 
OF SLENDER CRUCIFORM -WING ARRANGEMENTS 
AND THEIR WAKES . John R. Spreiter and Alvin H. 
Sacks. 1957. ii, 31p. diagrs., photos., tabs. 
(NACARept. 1296. Supersedes TN 3528) 



LINEARIZED LIFTING -SURFACE AND LIFTING - 
LINE EVALUATIONS OF SIDEWASH BEHIND ROLL- 
ING TRIANGULAR WINGS AT SUPERSONIC SPEEDS. 
Percy J. Bobbin. 1957. ii, 19p. diagrs., photo. 
(NACARept. 1301. Supersedes TN 3609) 



DETERMINATION OF VORTEX PATHS BY SERIES 
EXPANSION TECHNIQUE WITH APPLICATION TO 
CRUCIFORM WINGS . Alberta Y . Alksne . 1957. 
ill, 13p. diagrs., photos. (NACARept. 1311. 
Supersedes TN 3670) 



INDUCED VELOCITIES NEAR A LIFTING ROTOR 
WITH NONUNIFORM DISK LOADING. Harry H. 
HeysonandS. Katzott. 1957. iii, 88p. diagrs., 
photos., tab. (NACARept. 1319. Supersedes 
TN 3690; TN 3691) 



THEORETICAL AND EXPERIMENTAL INVESTIGA- 
TION OF THE SUBSONIC-FLOW FIELDS BENEATH 
SWEPT AND UNSWEPT WINGS WITH TABLES OF 
VORTEX-INDUCED VELOCITIES. William J. 
Alford, Jr. 1957. ii, 43p. diagrs., photo., tabs. 
(NACA Rept. 1327. Supersedes TN 3738) 



INVESTIGATION OF DOWNWASH, SIDEWASH, AND 
MACH NUMBER DISTRIBUTION BEHIND A RECTAN- 
GULAR WING AT A MACH NUMBER OF 2.41. 
David Adamson and William B. Boatright. 1957. 
ii, 57p. diagrs., photos., tab. (NACARept. 1340. 
Supersedes RM L50G12) 



THE SUBSONIC STATIC AERODYNAMIC CHARAC- 
TERISTICS OF AN AIRPLANE MODEL HAVING A 
TRIANGULAR WING OF ASPECT RATIO 3.1- EF- 
FECTS OF HORIZONTAL-TAH. LOCATION AND 
SIZE ON THE LONGITUDINAL CHARACTERISTICS. 
Bruce E. Tinling and Armando E. Lopez. July 1957. 
85p. diagrs., photo., tabs. (NACA TN 4041. Super- 
sedes RM A53L15) 



EXPERIMENTAL INVESTIGATION OF LIFT, DRAG, 
AND PITCHING MOMENT OF FIVE ANNULAR AIR- 
FOILS. Hermans. Fletcher. October 1957. 
25p. diagrs., photos. (NACA TN 4117) 



DATA FROM FLOW-FIELD SURVEYS BEHIND A 
LARGE-SCALE THIN STRAIGHT WING OF ASPECT 
RATIO 3. William T. Evans. June 1958. 13p. 
diagrs. (NACA RM A58D17) 



(1.2.2.8) 
BOUNDARY LAYER 



A SUMMARY AND ANALYSIS OF THE LOW-SPEED 
LONGITUDINAL CHARACTERISTICS OF SWEPT 
WINGS AT HIGH REYNOLDS NUMBER. G. Chester 
Furlong and James G. McHugh. 1957. iii, 149p. 
diagrs., tabs. (NACA Rept. 1339. Supersedes 
RM L52D16) 



ON POSSIBLE SIMILARITY SOLUTIONS FOR 
THREE-DIMENSIONAL INCOMPRESSIBLE LAMINAR 
BOUNDARY-LAYER FLOW OVER DEVELOPABLE 
SURFACES AND WITH PROPORTIONAL MAIN- 
STREAM VELOCITY COMPONENTS. Arthur G. 
Hansen, Case Institute of Technology. September 
1958. (ii), 79p. diagrs. (NACA TM 1437) 



SOME NUMERICAL SOLUTIONS OF SIMILARITY 
EQUATIONS FOR THREE-DIMENSIONAL LAMINAR 
INCOMPRESSIBLE BOUNDARY -LAYER FLOWS. 
Peggy L. Yohner and Arthur G. Hansen. September 
1958. 76p. diagrs., tabs. (NACA TN 4370) 



(1.2.2.8.1) 
Characteristics 



EFFECTS OF SPOILER AILERONS ON THE AERO- 
DYNAMIC LOAD DISTRIBUTION OVER A 45° * 
SWEPTBACK WING AT MACH NUMBERS FROM 0.60 
TO 1.03. Joseph M. Hallissy, Jr., F. E. West, Jr., 
and George Liner. May 1954. 162p. diagrs., tabs. 
(NACA RM L54C17a) 



EFFECTS OF FDQNG TRANSITION ON THE TRAN- 
SONIC AERODYNAMIC CHARACTERISTICS OF A 
WING-BODY CONFIGURATION AT REYNOLDS NUM- 
BERS FROM 2.4 TO 12 MILLION. Lynn W. Hunton. 
July 1958. 56p. diagrs. (NACA TN 4279) 



69 



(1) AERODYNAMICS 



(1.2.2.8.2) 

Control 



INVESTIGATION OF THE USE OF AREA SUCTION 
TO INCREASE THE EFFECTIVENESS OF 
TRAILING-EDGE FLAPS OF VARIOUS SPANS ON 
A WING OF 45° SWEEPBACK AND ASPECT RATIO 
6. Roy N. Griffin, Jr., and David H. Hickey. 
June 1956. 64p. diagrs., photo., tabs. 
(NACA RM A56B27) 



THE USE OF AREA SUCTION FOR THE PURPOSE 
OF IMPROVING THE LONGITUDINAL CHARACTER- 
ISTICS OF A THIN UNSWEPT-WING MODEL 
EQUIPPED WITH LEADING- AND TRAILING-EDGE 
FLAPS. David G. Koenig. July 1956. 52p. 
diagrs., photo., tabs. (NACA RM A56D23) 



BLOWING OVER THE FLAPS AND WING LEADING 
EDGE OF A THIN 49° SWEPT WING-BODY -TAIL 
CONFIGURATION IN COMBINATION WITH LEADING- 
EDGE DEVICES. H. Clyde McLemore and Marvin P. 
Fink. July 1956. 57p. diagrs., photo. 
(NACA RM L56E16) 



APPLICATION OF AREA SUCTION TO LEADING- 
EDGE AND TRAILING-EDGE FLAPS ON A 44<> 
SWEPT -WING MODEL. Curt A. Holzhauser, Robert 
K. Martin, and V. Robert Page. September 1956. 
66p. diagrs., photos., tabs. (NACA RM A56F01) 



FULL-SCALE WIND-TUNNEL TESTS OF A 35° 
SWEPTBACK-WING AIRPLANE WITH HIGH- 
VELOCITY BLOWING OVER THE TRAILING-EDGE 
FLAPS - LONGITUDINAL AND LATERAL STABIL- 
ITY AND CONTROL. William H. Tolhurst, Jr., 
and Mark W. Kelly. October 1956. 64p. diagrs., 
photo., tabs. (NACA RM A56E24) 



WIND-TUNNEL TESTS OF BLOWING BOUNDARY- 
LAYER CONTROL WITH JET PRESSURE RATIOS 
UP TO 10 ON THE TRAILING-EDGE FLAPS OF A 
35° SWEPTBACK WING AIRPLANE. Mark W. Kelly 
and Jeffrey H. Tucker. October 1956. 24p. diagrs., 
photo., tab. (NACA RM A56G19) 



LARGE-SCALE WIND-TUNNEL TESTS OF AN AIR- 
PLANE MODEL WITH A 450 SWEPTBACK WING OF 
ASPECT RATIO 2.8 WITH AREA SUCTION APPLIED 
TO TRAILING-EDGE FLAPS AND WITH SEVERAL 
WING LEADING-EDGE MODIFICATIONS. David G 
Koenig and Kiyoshi Aoyagi. November 1956. 66p. 
diagrs., photo., tabs. (NACA RM A56H08) 



HIGH-PRESSURE BLOWING OVER FLAP AND WING 
LEADING EDGE OF A THIN LARGE-SCALE 49° 
SWEPT WING-BODY -TAIL CONFIGURATION IN 
COMBINATION WITH A DROOPED NOSE AND A 
NOSE WITH A RADIUS INCREASE. Marvin P. Fink 
andH. Clyde McLemore. May 1957. 40p. diagrs., 
photo. (NACA RM L57D23) 



AIR LOAD DISTRIBUTIONS ON A FLAPPED WING 

RESULTING FROM LEADING-EDGE AND TRA1LING- 
EDGE BLOWING. H. Clyde McLemore. June 1957. 
9p. diagrs. (NACA RM L57D23b) 



FLIGHT INVESTIGATION OF THE LOW-SPEED 
CHARACTERISTICS OF A 35 f J SWEPT-WING AIR- 
PLANE EQUIPPED WITH AN AREA-SUCTION 
EJECTOR FLAP AND VARIOUS WING LEADING- 
EDGE DEVICES. Seth B. Anderson, Alan E. Faye, 
Jr., and Robert C. Innis. September 1957. 28p. 
diagrs., photos., tab. (NACA RM A57G10) 



THE USE OF A LEADING-EDGE AREA-SUCTION 
FLAP AND LEADING-EDGE MODIFICATIONS TO 
IMPROVE THE HIGH-LIFT CHARACTERISTICS OF 
AN AIRPLANE MODEL WITH A WING OF 450 
SWEEP AND ASPECT RATIO 2.8. David G. Koenig 
and Kiyoshi Aoyagi. November 1957. 46p. diagrs., 
photo., tabs. (NACA RM A57H21) 



WIND-TUNNEL INVESTIGATION OF THE USE OF 
LEADING-EDGE AND TRAILING-EDGE AREA- 
SUCTION FLAPS ON A 13-PERCENT-THICK 
STRAIGHT WING AND FUSELAGE MODEL. Curt A. 
Holzhauser. January 1958. 26p. diagrs., photo., 
tabs. (NACA RM A57K01) 



LOW-SPEED BOUNDARY-LAYER-CONTROL 
INVESTIGATION ON A THIN RECTANGULAR SEMI- 
SPAN WING WITH LEADING-EDGE AND TRAILING- 
EDGE FLAPS. Delwin R. Croom and Thomas R. 
Turner. January 1958. 213p. diagrs., tabs. 
(NACA RM L57J15) 



SURFACE PRESSURE DISTRIBUTIONS ON A LARGE- 
SCALE 490 SWEPTBACK WING-BODY-TAIL CON- 
FIGURATION WITH BLOWING APPLIED OVER THE 
FLAPS AND WING LEADING EDGE. H. Clyde 
McLemore and Marvin P. Fink. February 1958. 
129p. diagrs., photo., tabs. (NACA RM L57K25) 



FULL-SCALE WIND-TUNNEL TESTS OF A 35° 
SWEPTBACK-WING AIRPLANE WITH BLOWING 
FROM THE SHROUD AHEAD OF THE TRAILING- 
EDGE FLAPS. William H. Tolhurst, Jr. July 
1958. 40p. diagrs., photos., tabs. (NACA TN 4283) 



LARGE-SCALE WIND-TUNNEL TESTS OF AN AIR- 
PLANE MODEL WITH AN UNSWEPT, ASPECT- 
RATIO-10WING, TWO PROPELLERS, AND AREA- 
SUCTION FLAPS. James A. Weiberg, Roy N. , 
Griffin, Jr., and George L. Florman, September 
1958. 76p. diagrs., photos., tab. (NACA TN 4365) a 



70 



(1) AERODYNAMICS 



(1.3) 
Bodies 



WIND-TUNNEL INVESTIGATION OF THE STABILITY 
OF THE JETTISONABLE NOSE SECTION OF THE 
XS-2 AIRPLANE. Stanley H. Scher and Roscoe H. 
Goodwin. October 14, 1948. 19p. diagrs., photos., 
tabs. (NACA RM L8I14) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR-ARC SECTIONS AND 40° SWEEPBACK. 
FORCE CHARACTERISTICS OF THE COMPLETE 
CONFIGURATION AND ITS VARIOUS COMPONENTS 
AT MACH NUMBERS OF 1.40 AND 1.59. Norman F. 
Smith and Jaok E. Marte. January 22, 1951. 55p. 
diagrs., photos., tab. (NACA RM L50K14) 



BASIC PRESSURE MEASUREMENTS ON A FUSE- 
LAGE AND A 45° SWEPTBACK WING-FUSELAGE 
COMBINATION AT TRANSONIC SPEEDS IN THE 
SLOTTED TEST SECTION OF THE LANGLEY 
8-FOOT HIGH-SPEED TUNNEL. Donald L. Loving 
and Claude V. WiUiams. September 1951. 59p. 
diasrs., photos. (NACA RM L51F05) 



FREE-SPINNING TUNNEL INVESTIGATION OF A 
1/20-SCALE MODEL OF THE DOUGLAS X-3 AIR- 
PLANE. Burton E. Hultz. December 26, 1951. 
23p. diagrs., photos., tab. (NACA RM L51K12) - 



AERODYNAMIC CHARACTERISTICS AT SUPER- 
SONIC SPEEDS OF A SERIES OF WING-BODY 
COMBINATIONS HAVING CAMBERED WINGS WITH 
AN ASPECT RATIO OF 3.5 AND A TAPER RATIO 
OF 0.2. EFFECTS OF SWEEP ANGLE AND THICK- 
NESS RATIO ON THE AERODYNAMIC CHARACTER- 
ISTICS IN PITCH AT M = 1.60. Ross B. Robinson 
and Cornelius Driver. January 1952. 27p. diagrs., 
photos., tabs. (NACA RM L51K16a) 



AERODYNAMIC CHARACTERISTICS AT SUPER- 
SONIC SPEEDS OF A SERIES OF WING-BODY COM- 
BINATIONS HAVING CAMBERED WINGS WITH AN 
ASPECT RATIO OF 3.5 AND A TAPER RATIO OF 
0.2. EFFECTS OF SWEEP ANGLE AND THICKNESS 
RATIO ON THE AERODYNAMIC CHARACTERISTICS 
IN PITCH AT M = 2.01. Ross B. Robinson. July 
1952. 27p. diagrs., photo., tabs. 
(NACA RM L52E09) 



EXPLORATORY ROCKET FLIGHT TESTS TO IN- 
VESTIGATE THE USE OF A FREELY SPINNING 
MONOPLANE TAIL FOR STABILIZING A BODY. 
Paul E. Purser and Joseph E. Stevens. October 
1952. 25p. diagrs., photos., tab. 
(NACA RM L52I05a) 



PRELIMINARY FREE-FUGHT INVESTIGATION OF 
THE ZERO-LIFT DRAG PENALTIES OF SEVERAL 
MISSILE NOSE SHAPES FOR INFRARED SEEKING 
DEVICES. Robert O. Piland. December 1952. 
22p. diagrs., photos. (NACA RM L52F23) 



AN* INVESTIGATION OF SOME FACTORS AFFECT- 
ING THE DRAG OF RELATIVELY LARGE NON- 
LIFTING BODIES OF REVOLUTION IN A SLOTTED 
TRANSONIC WIND TUNNEL. Robert E. Pendley 
and Carroll R. Bryan. January 1953. 52p. diagrs.,. 
photos., tabs. (NACA RM L52H22) 



INVESTIGATION AT TRANSONIC SPEEDS OF A 
FORWARD- LOCATED UNDERSLUNG AIR INLET 
ON A BODY OF REVOLUTION. P . Kenneth 
Pierpont and John A. Braden. January 1953. 
109p. diagrs., photos., tabs. (NACA RM L52K17) 



INVESTIGATION OF THE EFFECT OF SPANWISE 
POSITIONING OF A VERTICALLY SYMMETRIC 
OGIVE -CYLINDER NACELLE ON THE HIGH-SPEED 
AERODYNAMIC CHARACTERISTICS OF A 45° 
SWEPTBACK TAPERED-IN-THICKNESS WING OF 
ASPECT RATIO 6 WITH AND WITHOUT A FUSE- 
LAGE. H. Norman Silvers and Thomas J. King, Jr. 
October 1953. 62p. diagrs., tabs. 
(NACA RM L53H17) 



ZERO-LIFT DRAG OF SEVERAL CONICAL AND 
BLUNT NOSE SHAPES OBTAINED IN FREE FLIGHT 
AT MACH NUMBERS OF 0.7 TO 1.3. Robert O. 
Piland and Leonard W. Putland. March 1954. 14p. 
diagrs., photos., tab. (NACA RM L54A27) 



FLIGHT MEASUREMENTS OF AVERAGE SKIN- 
FRICTION COEFFICIENTS ON A PARABOLIC BODY 
OF REVOLUTION (NACA RM-10) AT MACH NUM- 
ERS FROM 1.0 TO 3.7. J. Dan Loposer and 
Charles B. Rumsey. August 1954. 32p. diagrs., 
photos. (NACA RM L54G14) 



INVESTIGATION OF SOME WAKE VORTEX CHAR- 
ACTERISTICS OF AN INCLINED OGIVE-CYLINDER 
BODY AT MACH NUMBER 1.98. Leland H. 
Jorgensen and Edward W. Perkins. August 1955. 
47p. diagrs., photos., tabs. (NACA RM A55E31) 



TRANSONIC WIND-TUNNEL INVESTIGATION OF 
EFFECTS OF WINDSHIELD SHAPE AND CANOPY 
LOCATION ON THE AERODYNAMIC CHARACTER- 
ISTICS OF CANOPY-BODY COMBINATIONS, Elden 
S. Cornette and Harold L. Robinson. September 
1955. 55p. diagrs. (NACA RM L55G08) 



INFLUENCE OF THE BODY FLOW FIELD ON THE 
ZERO-LIFT WAVE DRAG OF WING -BODY COMBI- 
NATIONS MODIFIED IN ACCORDANCE WITH THE 
TRANSONIC AREA RULE. William A. Page. 
February 1956. 26p. diagrs. (NACA RM A55K10) 



ACOUSTIC, THRUST, AND DRAG CHARACTERIS- 
TICS OF SEVERAL FULL-SCALE NOISE SUPPRES- 
SORS FOR TURBOJET ENGINES. Carl C. Ciepluch, 
Warren J. North, Willard D. Coles, and Robert J. 
Antl. April 1958. 48p. diagrs., photos. 
(NACA TN 4261) 



TRANSONIC DRAG OF SEVERAL JET -NOISE 
SUPPRESSORS. Warren J. North. April 1958. 34p. 
diagrs., photos. (NACA TN 4269) 



(1) AERODYNAMICS 



71 



(1.3.1) 
THEORY 



INVESTIGATION OF OFF-DESIGN PERFORMANCE 
UK S HOCK-IN -KOTOR TYPE SUPERSONIC 
BLADING. Robert C. Graham, John F. Klapproth, 
and Frank J. Barina. May 7, 1951. 25p. diagrs., 
photos. (NACA RM E51C22) 



AERODYNAMICS OF SLENDER BODIES AT MACH 
NUMBER OF 3.12 AND REYNOLDS NUMBERS 
FROM 2 x 106 TO 15 x 106. II - AERODYNAMIC 
LOAD DISTRIBUTIONS OF SERIES OF FIVE BODIES 
HAVING CONICAL NOSES AND CYLINDRICAL 
AFTERBODIES. John R. Jack and Lawrence I. 
Gould. May 1952. 28p. diagrs., photos., tabs. 
(NACA RM E52C10) 



A PRESSURE -DISTRIBUTION INVESTIGATION OF A 
FmENESS-RATIO-12.2 PARABOLIC BODY OF REV- 
OLUTION (NACA RM-10) AT M = 1.59 AND 
ANGLES OF ATTACK UP TO 36°. Morton Cooper, 
John P. Gapcynski, and Lowell E. Hasel. October 
1952. 89p. diagrs., photos., tabs. 
(NACA RM L52G14a) 



INVESTIGATION OF THE DRAG OF VARIOUS 
AXIALLY SYMMETRIC NOSE SHAPES OF FINENESS 
RATIO 3 FOR MACH NUMBERS FROM 1.24 TO 3.67. 
Edward W. Perkins and Leland H. Jorgensen. 
November 1952. 50p. diagrs., photos. 
(NACA RM A52H28) 



CORRELATION BY THE HYPERSONIC SIMILARITY 
RULE OF PRESSURE DISTRIBUTIONS AND WAVE 
DRAGS FOR MINIMUM-DRAG NOSE SHAPES AT 
ZERO ANGLE OF ATTACK. Leland H. Jorgensen. 
August 1953. 23p. diagrs. (NACA RM A53F12) 



INVESTIGATION OF SOME WAKE VORTEX CHAR- 
ACTERISTICS OF AN INCLINED OGIVE-CYLINDER 
BODY AT MACH NUMBER 1.98. Leland H. 
Jorgensen and Edward W. Perkins. August 1955. 
47p. diagrs., photos., tabs. (NACA RM A55E31) 



FREE-FLIGHT TESTS TO DETERMINE THE 
POWER -ON AND POWER -OFF PRESSURE DISTRI- 
BUTION AND DRAG OF THE NACA RM-10 RE- ■ 
SEARCH VEHICLE AT LARGE REYNOLDS NUM- 
BERS BETWEEN MACH NUMBERS 0.8 AND 3.0. 
Sherwood Hoffman. September 1955. 55p. diagrs., 
photos.. 3 tabs. (NACA RM L55H02) 



BODIES OF REVOLUTION HAVING MINIMUM DRAG 
AT HIGH SUPERSONIC AIRSPEEDS. A. J. Eggers, 
Jr., Meyer M. Resnlkoff, and David H. Dennis. 
1957. ii, 12p. diagrs., photos. (NACA Rept. 1306. 
Supersedes TN 3666) 



THREE-DIMENSIONAL TRANSONIC FLOW THEORY 
APPLIED TO SLENDER WINGS AND BODIES. 
Max. A. Heaslet and John R. Spreiter. 1957. 
iii, 29p. diagrs. (NACA Rept. 1318. Supersedes 
TN 3717) 



A SECOND-ORDER SHOCK-EXPANSION METHOD 
APPLICABLE TO BODIES OF REVOLUTION NEAR 
ZERO LIFT. Clarence A. Syvertson and David H. 
Dennis. 1957. ii, 20p. diagrs., tabs. 
(NACA Rept. 1328. Supersedes TN 3527) 



THE MINIMIZATION OF WAVE DRAG FOR WINGS 
AND BODIES WITH GIVEN BASE AREA OR 
VOLUME. Max. A. Heaslet. July 1957. 27p. 
(NACA TN 3289) 



A RAPID METHOD FOR PREDICTING ATTACHED- 
SHOCK SHAPE. Eugene S. Love and Ronald H. 
Long. October 1957. 34p. diagrs., tab. 
(NACA TN 4167) 



LAMINAR BOUNDARY LAYER WITH HEAT TRANS- 
FER ON A CONE AT ANGLE OF ATTACK IN A 
SUPERSONIC STREAM. Eli Reshotko. December 
1957. (i), 64p. diagrs., tabs. (NACA TN 4152) 



A REEXAMINATION OF THE USE OF SIMPLE 
CONCEPTS FOR PREDICTING THE SHAPE AND 
LOCATION OF DETACHED SHOCK WAVES. 

Eugene S. Love. December 1957. 53p. diagrs. 
(NACA TN 4170) 



EXTREME SPEEDS AND THERMODYNAMIC 
STATES IN SUPERSONIC FLIGHT. (Extreme 
Geschwindigkeiten und thermische Zustande beim 
Uberschallflug.) Klaus Oswatitsch. April 1958. 
39p. diagrs. . tabs. (NACA TM 1434. Translation 
from Zeitschrift fiir Flugwissenschaften, v,4, 
no. 3/4, 1956, p. 95-108) 



EXPERIMENTAL STUDY OF THE EQUIVALENCE 
OF TRANSONIC FLOW ABOUT SLENDER CONE- 
CYLINDERS OF CIRCULAR AND ELLDPTIC CROSS 
SECTION. William A. Page. April 1958. 45p. 
diagrs., photos., tab. (NACA TN 4233) 



A NUMERICAL METHOD FOR EVALUATING WAVE 
DRAG. Maurice S- Cahn and Walter B. Olstad. 
June 1958. 13p. diagrs., tabs. (NACA TN 4258) 



AERODYNAMIC RESEARCH ON FUSELAGES WITH 
RECTANGULAR CROSS SECTION . (Aerodynamische 
Untersuchungen an Rumpfen mit rechteckahnlichem 
Querschnitt.) K. Maruhn. July 1958. 37p. diagrs. 
(NACA TM 1414. Translation from Jahrbuch 1942 
der deutschen Luftfahrtforschung, p. 263-279.) 



SECOND-ORDER SLENDER-BODY THEORY - 
AXISYMMETRIC FLOW. Milton D. Van Dyke. 
September 1958. (i). 46p. (NACA TN 4281) 



A STUDY OF SEVERAL THEORETICAL METHODS 
FOR COMPUTING THE ZERO-LIFT WAVE DRAG 
OF A FAMILY OF OPEN-NOSED BODIES OF REVO- 
LUTION IN THE MACH NUMBER RANGE OF 2.0 TO 
4.0. Leroy L. Presley and Emmet A. Mossman. 
September 1958. 61p. diagrs. (NACA TN 4368) 



APPROXIMATE METHOD FOR CALCULATION OF J 
LAMINAR BOUNDARY LAYER WITH HEAT TRANS- 
FER ON A CONE AT LARGE ANGLE OF ATTACK 
IN SUPERSONIC FLOW. William E. Brunk. 
September 1958. 26p. diagrs., tab. (NACA TN 4380) 



72 



(1) AERODYNAMICS 



(1.3.2) 
SHAPE VARIABLES 



INVESTIGATION AT MACH NUMBER 1.91 OF SIDE 
AND BASE PRESSURE DISTRIBUTIONS OVER CONI- 
CAL BOATTAILS WITHOUT AND WITH JET FLOW 
ISSUING FROM BASE. Edgar M. Cortright, Jr., and 
Albert H-' Schroeder. September 1951. 59p. diagrs., 
photos. (NACA RM E51F26) 



FORCES AND MOMENTS ON POINTED AND BLUNT - 
NOSED BODIES OF REVOLUTION AT MACH NUM- 
BERS FROM 2.75 TO 5.00. David H. Dennis and 
Bernard E. Cunningham. August 1952. 47p. 
diagrs., photo., tabs. (NACA RM A52E22) 



INVESTIGATION OF THE DRAG OF BLUNT-NOSED 
BODIES OF REVOLUTION IN FREE FLIGHT AT 
MACH NUMBERS FROM 0.6 TO 2.3. Harvey A. 
Wallskog and Roger G. Hart. June 1953. 28p. 
diagrs., photos., tab. (NACA RM L53D14a) 



PRELIMINARY INVESTIGATION OF THE EFFECTS 
OF SEVERAL SEEKER-NOSE CONFIGURATIONS ON 
THE LONGITUDINAL CHARACTERISTICS OF A 
CANARD-TYPE MISSILE AT A MACH NUMBER OF 
1.60. A. Warner Robins. October 1953. 25p. 
diagrs., photos., tabs. (NACA RM L53I18) 



THE EFFECT OF NOSE RADIUS AND SHAPE ON 
THE AERODYNAMIC CHARACTERISTICS OF A 
FUSELAGE AND A WING-FUSELAGE COMBINATION 
AT ANGLES OF ATTACK. John P. Gapcynski and 
A. Warner Robins. October 1953. 23p. diagrs. 
(NACA RM L53I23a) 



TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF TAPER RATIO, BODY INDEN- 
TATION, FDCED TRANSITION, AND AFTERBODY 
SHAPE ON THE AERODYNAMIC CHARACTERIS- 
TICS OF A 45° SWEPTBACK WING-BODY COMBI- 
NATION. Francis G. Morgan, Jr., and Melvin M. 
Carmel. March 1954. 37p. diagrs., tab. 
(NACA RM L54A15) 



AERODYNAMIC CHARACTERISTICS OF TWO FLAT- 
BOTTOMED BODIES AT MACH NUMBER OF 3.12. 
John R. Jack and Barry Moskowitz. April 1954. 
9p. diagrs. (NACA RM E53Lllb) 



PRELIMINARY INVESTIGATION OF PUMPING AND 
THRUST CHARACTERISTICS OF FULL-SIZE 
COOLING-AIR EJECTORS AT SEVERAL EXHAUST- 
GAS TEMPERATURES. W. K. Greathouse. April 
1954. 130p. diagrs., photos., tab, 
(NACA RM E54A18) 



OPTIMUM LIFTING BODIES AT HIGH SUPERSONIC 
AIRSPEEDS. Meyer M. Resnikoff. May 1954. 
22p. diagrs., photo. (NACA RM A54B15) 



EXPERIMENTAL DATA FOR FOUR FULL-SCALE 
CONICAL COOLING-AIR EJECTORS. C. C. 
Ciepluch and D. B. Fenn. November 1954. 41p. 
diagrs., photo., tab. (NACA RM E54F02) 



EXPERIMENTAL INVESTIGATION OF DRAG OF 
AFTERBODIES WITH EXITING JET AT HIGH 
SUBSONIC MACH NUMBERS. Reino J. Salmi. 
November 1954. 28p. diagrs., photos. 
(NACA RM E54I13) 



A METHOD FOR DESIGNING LOW -DRAG NOSE- 
INLET-BODY COMBINATIONS FOR OPERATION 
AT MODERATE SUPERSONIC SPEEDS. Robert R. 
Howell. November 1954. 29p. diagrs., photos., 
tab. (NACARM L54I01a) 



EFFECTS OF SOME EXTERNAL-STORE MOUNTING 
ARRANGEMENTS AND STORE SHAPES ON THE 
BUFFET AND DRAG CHARACTERISTICS OF WING- 
LESS ROCKET-POWERED MODELS AT MACH NUM- 
BERS FROM 0.7 TO 1.4. Homer P. Mason and 
Allen B. Henning. December 1954. 45p. diagrs., 
photos., tabs. (NACA RM L54I20a) 



TRANSONIC LONGITUDINAL AERODYNAMIC 
EFFECTS OF SWEEPING UP THE REAR OF THE 
FUSELAGE OF A ROCKET-PROPELLED AIR- 
PLANE MODEL HAVING NO HORIZONTAL TAIL. 
James H. Parks. January 1955. 30p. diagrs., 
photo. (NACA RM L54K12) 



AN EXPERIMENTAL INVESTIGATION OF TWO 
METHODS FOR REDUCING TRANSONIC DRAG OF 
SWEPT-WING AND BODY COMBINATIONS. John B. 
McDevitt. April 1955. 27p. diagrs., photos. 
(NACA RM A55B21) 



TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF TAPER RATIO AND BODY IN- 
DENTATION ON THE AERODYNAMIC LOADING 
CHARACTERISTICS OF A 45<> SWEPTBACK WING 
IN THE PRESENCE OF A BODY. James B. Delano 
and John P. Mugler, Jr. April 1955. 53p. diagrs., 
photos., tab. (NACA RM L54L28) 



TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE AERODYNAMIC LOADING CHARACTERISTICS 
OF A 60° DELTA WING IN THE PRESENCE OF A 
BODY WITH AND WITHOUT INDENTATION. John 
P. Mugler, Jr. September 1955. 30p. diagrs., 
photos., tab. (NACARM L55G11) 



EXPERIMENTAL STUDY OF A METHOD OF DE- 
SIGNING THE SWEPTBACK- WING -FUSELAGE 
JUNCTURE TO REDUCE THE DRAG AT MODERATE 
SUPERSONIC SPEEDS. Robert R. Howell. January 
1956. 20p. diagrs., photos., tabs. 
(NACA RM L55H05a) 



TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF INCIDENCE AND BODY INDEN- 
TATION ON THE WING LOADS OF A 45° SWEPT. 
BACK WING-BODY COMBINATION. Robert J. 
Piatt, Jr. January 1956. 24p. diagrs., photos., 
tab. (NACA RM L55H26) 



TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE AERODYNAMIC LOADING CHARACTERISTICS 
OF A HIGHLY TAPERED UNSWEPT WING IN THE 
PRESENCE OF A BODY WITH AND WITHOUT IN- 
DENTATION. Joseph D. Brooks. February 1956. 
30p. diagrs., photos., tab. (NACA RM L55J20) 



73 



(1) AERODYNAMICS 



EFFECT OF WING SIZE AND AMOUNT OF INDEN- 
TATION ON APPLIC ABILITY OF TRANSONIC AREA 
RULE TO SWEPT-WING CONFIGURATIONS. 

James Rudyard Hall- July 1956. 33p. diagrs., 
photos., tabs. (NACA RM L55F03) 



EFFECT OF CAMBER ON THE DRAG OF A BODY 
OF REVOLUTION. Robert R. Dickey. October 
1956. ap. diagrs., tabs. (NACA RM A56E23) 



NONLIFTING WING -BODY COMBINATIONS WITH 
CERTAIN GEOMETRIC RESTRAINTS HAVING 
MINIMUM WAVE DRAG AT LOW SUPERSONIC 
SPEEDS. Harvard Lomax. 1957. ii, lip. diagrs. 
(NACARept. 1297. Supersedes TN 3667) 



STATUS OF SPIN RESEARCH FOR RECENT AIR- 
PLANE DESIGNS. Anshal I. Neihouse, Salter J. 
Klinar, and Stanley H. Scher. August 1957. ii, 
98p. diagrs., photos., tabs. (NACA RM L57F12) 



EFFECT OF NOSE SHAPE ON SUBSONIC AERO- 
DYNAMIC CHARACTERISTICS OF A BODY OF 
REVOLUTION HAVING A FINENESS RATIO OF 10.94. 
Edward C. Polhamus. August 1957. 29p. diagrs. 
(NACA RM L57F25) 



A STUDY OF THE MOTION AND AERODYNAMIC 
HEATING OF MISSILES ENTERING THE EARTH'S 
ATMOSPHERE AT HIGH SUPERSONIC SPEEDS. 
H. Julian Allen and A. J. Eggers, Jr. October 
1957. 61p. diagrs. (NACA TN 4047. Supersedes 
RM A53D28) 



COLLECTION OF ZERO-LIFT DRAG DATA ON 
BODIES OF REVOLUTION FROM FREE-FLIGHT 
INVESTIGATIONS. William E. Stoney, Jr. 
January 1958. 373p. diagrs., tabs. 
(NACA TN 4201) 



BOUNDARY-LAYER TRANSITION ON AN OPEN- 
NOSE CONE AT MACH 3.1. Paul F. Brlnich. 
February 1958. lip. diagrs. (NACA TN 4214) 



STAGNATION-POINT HEAT TRANSFER TO BLUNT 
SHAPES IN HYPERSONIC FLIGHT, INCLUDING 
EFFECTS OF YAW. A. J. Eggers, Jr., 
C. Frederick Hansen, and Bernard E. Cunningham. 
April 1958. 54p. diagr. (NACA TN 4229) 



EXPERIMENTAL INVESTIGATION OF THE DRAG 
OF FLAT PLATES AND CYLINDERS IN THE SLIP- 
STREAM OF A HOVERING ROTOR. John W. McKee 
and Rodger L. Naeseth. April 1958. 42p. diagrs., 
photos., tab. (NACA TN 4239) 



EFFECT OF FAVORABLE PRESSURE GRADIENTS 
ON TRANSITION FOR SEVERAL BODIES OF REVO- 
LUTION AT MACH 3.12. John R. Jack. July 1958. 
28p. diagrs., photo. (NACA TN 4313) 



WIND-TUNNEL INVESTIGATION OF THE HIGH- 
SUBSONIC STATIC LONGITUDINAL STABILITY 
CHARACTERISTICS OF SEVERAL WING-BODY CON- 
FIGURATIONS DESIGNED FOR HIGH LIFT-DRAG 
RATIOS AT A MACH NUMBER OF 1.4. Paul G. 
Fournier. July 1958. 42p. diagrs., photo., tab. 
(NACA TN 4340) 



(1.3.2. 1) 
FINENESS RATIO 



FORCES AND MOMENTS ON POINTED AND BLUNT - 
NOSED BODIES OF REVOLUTION AT MACH NUM- 
BERS FROM 2.75 TO 5.00. David H. Dennis and 
Bernard E. Cunningham. August 1952. 47p. 
diagrs., photo., tabs. (NACA RM A52E22) 



INVESTIGATION OF INTERFERENCE LIFT, DRAG, 
AND PITCHING MOMENT OF A SERIES OF REC- 
TANGULAR WING AND BODY COMBINATIONS AT 
MACH NUMBERS OF 1.62, 1.93, AND 2.41. Donald 
E. Coletti. August 1952. 74p. diagrs., tabs. 
(NACA RM L52E26) 



STABILITY OF BODIES OF REVOLUTION HAVING 
FINENESS RATIOS SMALLER THAN 1 .0 AND 
HAVTNG ROUNDED FRONTS AND BLUNT BASES. 
Stanley H. Scher and James S. Bowman, Jr. 
January 1953. 23p. diagrs., tabs. 
(NACA RM L52L08) 



INVESTIGATION OF THE DRAG OF BLUNT -NOSED 
BODIES OF REVOLUTION IN FREE FLIGHT AT 
MACH NUMBERS FROM 0.6 TO 2.3. Harvey A. 
Wallskog and Roger G. Hart. June 1953. 28p. 
diagrs., photos., tab. (NACA RM L53D14a) 



CORRELATION BY THE HYPERSONIC SIMILARITY 
RULE OF PRESSURE DISTRIBUTIONS AND WAVE 
DRAGS FOR MINIMUM-DRAG NOSE SHAPES AT 
ZERO ANGLE OF ATTACK. Leland H. Jorgensen- 
August 1953. 23p. diagrs. (NACA RM A53F12) 



SOME EXPERIMENTAL EFFECTS OF AFTERBODY 
SHAPE ON THE ZERO-LIFT DRAG OF BODIES FOR 
MACH NUMBERS BETWEEN 0.8 AND 1.3. William 
E. Stoney, Jr. October 1953. 24p, diagrs., photos. 
(NACA RM L53I01) 



A WIND-TUNNEL INVESTIGATION OF THE USE 
OF SPOILERS FOR OBTAINING STATIC LONGITU- 
DINAL STABILITY OF A CANARD-MISSILE MODEL 
IN REVERSE FLIGHT. Hermans. Fletcher. June 
1954. 15p. diagrs., tab. (NACA RM L54E05) 



FREE-FLIGHT DETERMINATION OF FORCE AND 
STABILITY CHARACTERISTICS OF AN INCLINED 
BODY OF FINENESS RATIO 16.9 AT A MACH NUM- 
BER OF 174. Warren Gillespie, Jr. November 
1954. 17p. diagrs., photos., tab. 
(NACA RM L54G28a) 



EFFECT OF AIRPLANE CONFIGURATION ON 
STATIC STABILITY AT SUBSONIC AND TRANSONIC 
SPEEDS. Edward C. Polhamus and Joseph M. 
Hallissy, Jr. May 1956. 17p. diagrs. 
(NACA RM L56A09a) 



A SECOND-ORDER SHOCK- EXPANSION METHOD 
APPLICABLE TO BODIES OF REVOLUTION NEAR 
ZERO LIFT. Clarence A. Syvertson and David H. 
Dennis. 1957. ii, 20 p. diagrs., tabs. 
(NACA Rept. 1328. Supersedes TN 3527) 



74 



(1) AERODYNAMICS 



COLLECTION OF ZERO-LIFT DRAG DATA ON 
BODIES OF REVOLUTION FROM FREE-FLIGHT 
INVESTIGATIONS. William E. Stoney, Jr. 
January 1958. 373p. diagrs., tabs. 
(NACA TN 4201) 



PRESSURE DISTRIBUTIONS AT TRANSONIC SPEEDS 
FOR PARABOLIC -ARC BODIES OF REVOLUTION 
HAVING FINENESS RATIOS OF 10, 12, AND 14. 
Robert A« Taylor and John B. McDevitt. March 
1958. 80p. diagrs., photo. (NACA TN 4234) 



AN INVESTIGATION OF SUPERSONIC TURBULENT 
BOUNDARY LAYERS ON SLENDER BODIES OF 
REVOLUTION IN FREE FLIGHT BY USE OF A 
MACH-ZEHNDER INTERFEROMETER AND SHADOW- 
GRAPHS. Alvin Seiff and Barbara J. Short. 
September 1958. 57p. diagrs., photos. 
(NACA TN 4364) 



A STUDY OF SEVERAL THEORETICAL METHODS 
FOR COMPUTING THE ZERO-LIFT WAVE DRAG 
OF A FAMILY OF OPEN -NOSED BODIES OF REVO- 
LUTION IN THE MACH NUMBER RANGE OF 2.0 TO 
4.0. Leroy L. Presley and Emmet A. Mossman. 
September 1958. 61p. diagrs. (NACA TN 4368) 



(1.3.2.2) 
CROSS SECTION 



EXPERIMENTAL PRESSURE DISTRIBUTION ON AN 
ASYMMETRICAL NONCONICAL BODY AT MACH 
NUMBER 1.90. DeMarquis D. Wyatt. February 24, 

1949. 58p. diagrs., photos., tabs. 
(NACA RM E9B03) 



COMPARISON OF THEORETICAL AND EXPERI- 
MENTAL ZERO-LIFT DRAG-RISE CHARACTERIS- 
TICS OF WING-BODY-TAIL COMBINATIONS NEAR 
THE SPEED OF SOUND. George H. Holdaway. 
October 1953. 27p. diagrs., tab. 
(NACA RM A53H17) 



OPTIMUM LIFTING BODIES AT HIGH SUPERSONIC 
AIRSPEEDS. Meyer M. Resnikoff. May 1954. 
22p. diagrs., photo. (NACA RM A54B15) 



AN EXPERIMENTAL INVESTIGATION OF REDUC- 
TION IN TRANSONIC DRAG RISE AT ZERO LIFT BY 
THE ADDITION OF VOLUME TO THE FUSELAGE 
OF A WING -BODY -TAIL CONFIGURATION AND A 
COMPARISON WITH THEORY. George H. Holdaway. 
August 1954. 35p. diagrs., photos., tabs. 
(NACA RM A54F22) 



AN EXPERIMENTAL INVESTIGATION AT A MACH 
NUMBER OF 2.01 OF THE EFFECTS OF BODY 
CROSS-SECTION SHAPE ON THE AERODYNAMIC 
CHARACTERISTICS OF BODIES AND WING-BODY 
COMBINATIONS. Harry W. Carlson and John P. 
Gapcynski. July 1955. 29p. diagrs., tabs. 
(NACA RM L55E23) 



WIND-TUNNEL INVESTIGATION AT HIGH SUBSONIC 
SPEEDS OF SOME EFFECTS OF FUSELAGE CROSS- 
SECTION SHAPE AND WING HEIGHT ON THE STAT- 
IC LONGITUDINAL AND LATERAL STABILITY 
CHARACTERISTICS OF A MODEL HAVING A 45° 
SWEPT WING. Thomas J. King, Jr. February 
1956. 61p. diagrs., photo. (NACA RM L55J25) 



EFFECT OF AIRPLANE CONFIGURATION ON 
STATIC STABILITY AT SUBSONIC AND TRANSONIC 
SPEEDS. EdwardC. Polhamus and Joseph M. 
Hallissy, Jr. May 1956. 17p. diagrs. 
(NACA RM L56A09a) 



ELLIPTIC CONES ALONE AND WITH WINGS AT 
SUPERSONIC SPEEDS. Leland H. Jorgensen. 
October 1957. 55p. diagrs., photos. 
(NACA TN 4045) 



EFFECT OF FLOW INCIDENCE AND REYNOLDS 
NUMBER ON LOW-SPEED AERODYNAMIC CHAR- 
ACTERISTICS OF SEVERAL NONCIRCULAR CYL- 
INDERS WITH APPLICATIONS TO DIRECTIONAL 
STABILITY AND SPINNING. Edward C. Polhamus. 
January 1958. 54p. diagrs., photo., tab. 
(NACA TN 4176) 



AERODYNAMIC RESEARCH ON FUSELAGES WITH 
RECTANGULAR CROSS SECTION. (Aerodynamische 
Untersuchungen an Rumpfen mit rechteckahnlichem 
Querschnitt.) K. Maruhn. July 1958. 37p. diagrs. 
(NACA TM 1414. Translation from Jahrbuch 1942 
der deutschen Luftfahrtforschung, p. 263-279.) 



WIND-TUNNEL INVESTIGATION OF EFFECTS OF 
SPOILER LOCATION, SPOILER SIZE, AND FUSE- 
LAGE NOSE SHAPE ON DIRECTIONAL CHARACTER- 
ISTICS OF A MODEL OF A TANDEM-ROTOR HELI- 
COPTER FUSELAGE . James L. Williams. July,. 
1958. 44p. diagrs., photos., tab. (NACA TN 4305) 



FORCE AND PRESSURE MEASUREMENTS AT 
TRANSONIC SPEEDS FOR SEVERAL BODIES HAVING 
ELLIPTICAL CROSS SECTIONS. John B. McDevitt 
and Robert A. Taylor. September 1958. 152p. 
diagrs., photo., tab. (NACA TN 4362) 



(1.3.2.3) 
THICKNESS DISTRIBUTION 



INVESTIGATION OF THE DRAG OF VARIOUS 
AXIALLY SYMMETRIC NOSE SHAPES OF FINENESS 
RATIO 3 FOR MACH NUMBERS FROM 1,24 TO 3.67. 
Edward W. Perkins and Leland H. Jorgensen. 
November 1952. 50p. diagrs., photos. 
(NACA RM A52H28) 



INVESTIGATION OF THE DRAG OF BLUNT -NOSED 
BODIES OF REVOLUTION IN FREE FLIGHT AT 
MACH NUMBERS FROM 0.6 TO 2.3. Harvey A. 
Wallskog and Roger G. Hart. June 1953. 28p. 
diagrs., photos., tab. (NACA RM L53D14a) 



CORRELATION BY THE HYPERSONIC SIMILARITY 
RULE OF PRESSURE DISTRIBUTIONS AND WAVE 
DRAGS FOR MINIMUM-DRAG NOSE SHAPES AT 
ZERO ANGLE OF ATTACK. Leland H. Jorgensen. 
August 1953. 23p. diagrs. (NACA RM A53F12) 



SOME EXPERIMENTAL EFFECTS OF AFTERBODY 
SHAPE ON THE ZERO-LIFT DRAG OF BODIES FOR 
MACH NUMBERS BETWEEN 0.8 AND 1.3. William 
E. Stoney, Jr. October 1953. 24 p. diagrs., photos. 
(NACA RM L53I01) 



75 



{ 1 ) AERODYNAMICS 



TRANSONIC DRAG MEASUREMENTS OF EIGHT 
BODY-NOSE SHAPES. William E. Stoney, Jr. 
February 1954. !4p. diagrs., photos. 
(NACA RM L53K17) 



OPTIMUM LIFTING BODIES AT HIGH SUPERSONIC 
AIRSPEEDS. Meyer M. Resnikoff. May 1954. 
22p. dlagrs., photo. (NACA RM A54B15) 



INVESTIGATION OF THE EFFECTS OF BODY 
INDENTATION AND OF WING-PLAN-FORM 
MODIFICATION ON THE LONGITUDINAL CHARAC- 
TERISTICS OF A 60° SWEPT -WING-BODY COMBI- 
NATION AT MACH NUMBERS OF 1.41, 1.61, AND 
2.01. John R. Sevier, Jr. July 1955. 37p. diagrs., 
tab. (NACA RM L55E17) 



THEORETICAL CALCULATIONS OF SUPERSONIC 
WAVE DRAG AT ZERO LIFT FOR A PARTICULAR 
STORE ARRANGEMENT. Kenneth Margolis, 
Frank S. Malvestuto, Jr., and Peter J, Maxie, Jr. 
January 1958. 37p. dlagrs., tab. (NACA TN 4120) 



PRESSURE DISTRIBUTIONS AT TRANSONIC SPEEDS 
FOR SLENDER BODIES HAVING VARIOUS AXIAL 
LOCATIONS OF MAXIMUM DIAMETER. John B. 
McDevitt and Robert A. Taylor. July 1958. 112p. 
diagrs. , photo. (NACA TN 4280) 



(1.3.2.4) 
SURFACE CONDITIONS 



MEASUREMENTS OF AERODYNAMIC HEATING 
OBTAINED DURING DEMONSTRATION FLIGHT 
TESTS OF THE DOUGLAS D-558-H AIRPLANE. 
Ira P. Jones, Jr. November 1952. 19p. dlagrs., 
photo., tab. (NACA RM L5 2126a) 



EXPLORATORY INVESTIGATION OF TRANSPIRA- 
TION COOLING TO ALLEVIATE AERODYNAMIC 
HEATING ON AN 8° CONE IN A FREE JET AT A 
MACH NUMBER OF 2.05. William J . O'Sullivan, 
Loo T. Chauvin, and Charles B. Rumsey. September 
1953. 26p. diagrs, photos. (NACA RM L53H06)/ 



THE EFFECT OF SOME SURFACE ROUGHNESS 
ELEMENTS ON THE DRAG OF A BODY OF REVO- 
LUTION AT SUPERSONIC SPEEDS. Russell N. 
Hopko. November 1954. 14p. diagrs., photos., tab. 
(NACA RM L54I21) 



EXPLORATORY TESTS OF TRANSPIRATION COOL- 
ING OF A POROUS 80 CONE AT M = 2.05 USING. 
NITROGEN GAS, HELIUM GAS, AND WATER AS 
THE COOLANTS. Leo T. Chauvin and Howard S. 
Carter. June 1955. 22p. diagrs., photos., tab. 
(NACA RM L55C29) 



EFFECT OF MACH NUMBER ON BOUNDARY - 
LAYER TRANSITION IN THE PRESENCE OF PRES- 
SURE RISE AND SURFACE ROUGHNESS ON AN 
OGIVE -CYLINDER BODY WITH COLD WALL 
CONDITIONS. Robert J. Carros. April 1956. 
30p. diagrs . , photos . (NACA RM A56B1 5) 



EXPERIMENTAL INVESTIGATION OF INTERFER- 
ENCE EFFECTS OF LATERAL-SUPPORT STRUTS 
ON AFTERBODY PRESSURES AT MACH 1.9. John 
L. Klann and Ronald G. Huff. May 1956. 13p. 
diagrs., tab. (NACA RM E56C16) 



HEAT TRANSFER AND BOUNDARY -LAYER TRAN- 
SITION ON TWO BLUNT BODIES AT MACH NUMBER 
3.12. N. S. Diaconls, Richard J. Wisniewskl, and 
John R. Jack. October 1957. 31p. diagrs., photo. 
(NACA TN 4099) 



EXPERIMENTAL DROPLET IMPINGEMENT ON 
FOUR BODIES OF REVOLUTION. James P. Lewis 
and Robert S. Rugger i. December 1957. 61p. 
diagrs. , photos. (NACA TN 4092) 



INVESTIGATION OF EFFECTS OF DISTRIBUTED 
SURFACE ROUGHNESS ON A TURBULENT BOUND- 
ARY LAYER OVER A BODY OF REVOLUTION AT A 
MACH NUMBER OF 2.01. John R. Sevier, Jr., and 
K. R. Czarnecki. February 1958. 31p. dlagrs., 
photos. (NACA TN 4183) 



EFFECT OF DISTRIBUTED GRANULAR-TYPE 
ROUGHNESS ON BOUNDARY-LAYER TRANSITION 
AT SUPERSONIC SPEEDS WITH AND WITHOUT SUR- 
FACE COOLING. Albert L. Braslow. March 
1958. 22p. diagrs., photos. (NACA RM L58A17) 



EFFECTS OF FABRICATION-TYPE ROUGHNESS ON 
TURBULENT SKIN FRICTION AT SUPERSONIC 
SPEEDS. K. R. Czarnecki, John R. Sevier, Jr., 
and Melvin M. Carmel. July 1958. 15p. diagrs. 
(NACA TN 4299) 



EFFECTS OF BOUNDARY-LAYER DISPLACEMENT 
AND LEADING-EDGE BLUNTNESS ON PRESSURE 
DISTRIBUTION, SKIN FRICTION, AND HEAT TRANS- 
FER OF BODIES AT HYPERSONIC SPEEDS. 
Mite he I H. Bertram and Arthur Henderson, Jr. 
July 1958. 33p. diagrs. (NACA TN 4301) 



THEORETICAL DISTRIBUTION OF LAMINAR- 
BOUNDARY- LAYER THICKNESS, BOUNDARY- 
LAYER REYNOLDS NUMBER AND STABILITY . 
LIMIT, AND ROUGHNESS REYNOLDS NUMBER FOR 
A SPHERE AND DISK IN INCOMPRESSIBLE FLOW. 
Neal Tetervin. September 1958. 36p, diagrs. 
(NACA TN 4350) 



SIMPLIFIED METHOD FOR DETERMINATION OF 
CRITICAL HEIGHT OF DISTRIBUTED ROUGHNESS 
PARTICLES FOR BOUNDARY-LAYER TRANSITION 
AT MACH NUMBERS FROM TO 5. Albert L. 
Braslow and Eugene C. Knox. September 1958. 
18p. diagrs., photos. (NACA TN 4363) 



(1.3.2.5) 
PROTUBERANCES 



EXPERIMENTAL PRESSURE DISTRIBUTION ON AN 
ASYMMETRICAL NONCONICAL BODY AT MACH 
NUMBER 1.90. DeMarquis D. Wyatt. February 24, 
1949. 58p. diagrs., photos., tabs. 
(NACA RM E9B03) 



7b 



(1) AERODYNAMICS 



INFLUENCE OF FUSELAGE-MOUNTED ROCKET- 
BOOSTERS ON FLOW FIELD AT INLET AND ON 
DIFFUSER PERFORMANCE OF STRUT-MOUNTED 
ENGINE AT MACH NUMBERS OF 1.8 AND 2.0. 
George A. Wise and Leonard J. Obery. October 
1952. 16p. dlagrs., photos. (NACA RM E52I02) 



EFFECT ON TRANSONIC AND SUPERSONIC DRAG 
OF FUSELAGE GLOVES DESIGNED TO GIVE A 
SMOOTH OVERALL AREA DISTRIBUTION TO A 
SWEPT- WING -BODY COMBINATION. James 
Rudyard Hall. November 1954. lOp. dlagrs., 
nhotos. 'NACA RM L54H30) 



THE EFFECT OF SOME SURFACE ROUGHNESS 
ELEMENTS ON THE DRAG OF A BODY OF REVO- 
LUTION AT SUPERSONIC SPEEDS. Russell N. 
Hopko, November 1954. 14p. dlagrs., photos., tab. 
(NACA RM L54I21) 



RECOVERY TEMPERATURES AND HEAT TRANS- 
FER NEAR TWO-DIMENSIONAL ROUGHNESS 
ELEMENTS AT MACH 3.1. Paul F. Brlnich. 
February 1958. 20p. dlagrs. (NACA TN 4213) 



EFFECT OF SOME EXTERNAL CROSSWISE STIFF- 
ENERS ON THE HEAT TRANSFER AND PRESSURE 
DISTRIBUTION ON A FLAT PLATE AT MACH NUM- 
BERS OF 0.77, 1.39, AND 1.98. Howards. Carter. 
September 1958. 21p. diagrs., photo., tab. 
(NACA TN 4333) 



(1.3.3) 
CANOPIES 



ESTIMATED TRANSONIC FLYING QUALITIES OF A 
TAILLESS AIRPLANE BASED ON A MODEL INVES- 
TIGATION. Charles J. Donlan and Richard E. Kuhn. 
June 8, 1949. 63p. diagrs., photos., tabs. 
(NACA RM L9D08) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR-ARC SECTIONS AND 40° SWEEPBACK. 
FORCE CHARACTERISTICS OF THE COMPLETE 
CONFIGURATION AND ITS VARIOUS COMPONENTS 
AT MACH NUMBERS OF 1.40 AND 1.59. Norman F. 
Smith and Jack E. Marte. January 22, 1951. 55p. 
diagrs., photos., tab. {NACA RM L50K14) 



MEASUREMENTS OF AERODYNAMIC HEATING 
OBTAINED DURING DEMONSTRATION FLIGHT 
TESTS OF THE DOUGLAS D-558-II AIRPLANE. 
Ira P. Jones, Jr. November 1952. I9p. diagrs., 
photo., tab. (NACA RM L52I26a) 



THE EFFECT OF CANOPY LOCATION ON THE 
AERODYNAMIC CHARACTERISTICS OF A SWEPT- 
BACK WING-BODY CONFIGURATION AT TRAN- 
SONIC SPEEDS. Harold L. Robinson. June 1954. 
14p. diagrs., photo. (NACA RM L54E11) 



TRANSONIC WIND-TUNNEL INVESTIGATION OF 
EFFECTS OF WINDSHIELD SHAPE AND CANOPY 
LOCATION ON THE AERODYNAMIC CHARACTER- 
ISTICS OF CANOPY -BODY COMBINATIONS. Elden 
S. Cornette and Harold L. Robinson. September 
1955. 55p. diagrs. (NACA RM L55G08) 



FREE-FLIGHT INVESTIGATION TO DETERMINE 
THE DRAG OF FLAT- AND VEE-WINDSHIELD 
CANOPIES ON A PARABOLIC FUSELAGE WITH 
AND WITHOUT TRANSONIC INDENTATION 
BETWEEN MACH NUMBERS OF 0.75 AND 1.35. 
Walter L. Kouyoumjian and Sherwood Hoffman. 
September 1958. 34p. diagrs., photos., tabs. 
(NACA TN 4405) 



(1.3.4) 
DUCTED BODIES 



TRANSONIC FREE-FLIGHT DRAG RESULTS OF 
FULL-SCALE MODELS OF 16-INCH-DIAMETER 
RAM-JET ENGINES. Wesley E. Messing and 
LorenW. Acker. April 1952. 17p. diagrs. 
(NACARM E52B19) 



TRANSONIC FREE -FLIGHT INVESTIGATION OF THE 
TOTAL DRAG AND OF THE COMPONENT DRAGS 
(COWL PRESSURE, ADDITIVE, BASE, FRICTION, 
AND INTERNAL) ENCOUNTERED BY A 16-INCH- 
DIAMETER RAM -JET ENGINE FOR MACH NUMBERS 
FROM 0.80 TO 1.43. Wesley E. Messing and 
Leonard Rabb. August 1952. 34p. diagrs., photos. 
(NACA RM E52F02) 



TRANSONIC FLIGHT TESTS TO DETERMINE ZERO- 
LIFT DRAG AND PRESSURE RECOVERY OF NA- 
CELLES LOCATED AT THE WING ROOT ON A 45° 
SWEPTBACK WING AND BODY CONFIGURATION. 
Sherwood Hoffman and Austin L. Wolff. September 
1953. 31p. diagrs., photos., tabs. 
(NACA RM L53H20) 



JET EFFECTS ON FLOW OVER AFTERBODIES IN 

SUPERSONIC STREAM. Edgar M. Cortright, Jr., 
and Fred D. Kochendorfer . November 1953. 31p. 
diagrs., photos. (NACARM E53H25) 



FLIGHT INVESTIGATION OF ENGINE NACELLES 
AND WING VERTICAL POSITION ON THE DRAG OF 
A DELTA -WING AIRPLANE CONFIGURATION 
FROM MACH NUMBER 0.8 TO 2.0. Joseph H. Judd. 
March 1954. 39p. diagrs., photos., tabs. 
(NACA RM L53L21) 



PUMPING AND DRAG CHARACTERISTICS OF AN 
AIRCRAFT EJECTOR AT SUBSONIC AND SUPER- 
SONIC SPEEDS. Gerald C. Gorton. June 1954. 
19p. diagrs. (NACA RM E54D06) 



DRAG DATA FOR 16-INCH-DIAMETER RAM -JET 
ENGINE WITH DOUBLE -CONE INLET IN FREE 
FLIGHT AT MACH NUMBERS FROM 0.7 TO 1.8. 
Merle L. Jones, Leonard Rabb, and Scott H. 
Simpkinson. October 1954. 52p. diagrs., photos. 
(NACA RM E54H02) 



(I) AERODYNAMICS 



77 



(1.3.4.1) 
NOSE SHAPE 



FORCE AND PRESSURE CHARACTERISTICS FOR A 
SERIES OF NOSE INLETS AT MACH NUMBERS 
FROM 1.59 TO 1.99. I - CONICAL SPIKE ALL- 
EXTERNAL COMPRESSION INLET WITH SUBSONIC 
COWL LIP. Fred T. Esenweln and Alfred S. 
Valerino. January 19, 1951. 73p. diagrs., photos., 
tabs. (NACA RM E50J26) 



FORCE AND PRESSURE CHARACTERISTICS FOR A 
SERIES OF NOSE INLETS AT MACH NUMBERS 
FROM 1.59 TO 1.99. II - ISENTROPIC-SPKE ALL- 
EXTERNAL COMPRESSION INLET. L. J. Obery 
andG. W. Englert. February 9, 1951. 67p. 
diagrs-, photos., tabs. (NACA RM E50J 26a) 



FORCE AND PRESSURE CHARACTERISTICS FOR A 
SERIES OF NOSE INLETS AT MACH NUMBERS 
FROM 1.59 TO 1.99. IH - CONICAL-SPDCE ALL- 
EXTERNAL-COMPRESSION INLET WITH SUPER- 
SONIC COWL LIP. Maynard I. Weinstein and Joseph 
Davids. February 14, 1951. 51p. diagrs., tabs. 
(NACA RM E50J30) 



FORCE AND PRESSURE CHARACTERISTICS FOR A 
SERIES OF NOSE INLETS AT MACH NUMBERS 
FROM 1.59 TO 1.99. IV - CONICAL-SPIKE 
EXTERNAL-INTERNAL COMPRESSION INLET 
UTILIZING PERFORATED COWL. Robert T. 
Madden and Erail J. Kremzier. March 28, 1951. 
46p. diagrs., photos., tabs. (NACA RM E51B05) 



NACA INVESTIGATIONS OF ICING -PROTECTION 
SYSTEMS FOR TURBOJET -ENGINE INSTALLA- 
TIONS. Uwe von Glahn, Edmund E. Callaghan, and 
Vernon H. Gray. May 2, 1951. (ii), 83p. diagrs., 
photos. (NACA RM E51B12) 



TOTAL-PRESSURE RECOVERY OF A CIRCULAR 
UNDERSLUNG INLET WITH THREE DIFFERENT 
NOSE SHAPES AT A M\CH NUMBER OF 1.42. 
Charles F. Merlet and Howard S. Carter. February 
1952. 37p. diagrs., photos. (NACA RM L51K05) 



PRELIMINARY INVESTIGATION OF EFFECT OF 
ANGLE OF ATTACK ON PRESSURE RECOVERY 
AND STABILITY CHARACTERISTICS FOR A 
VERTICAL-WEDGE-NOSE INLET AT MACH NUM- 
BER OF 1.90. L. Abbott Leissler and Donald P. 
Hearth. August 1952. lip. diagrs., photos. 
(NACA RM E52E14) 



FORCE AND PRESSURE RECOVERY CHARACTER- 
ISTICS AT SUPERSONIC SPEEDS OF A CONICAL 
SPIKE INLET WITH BYPASSES DISCHARGING IN 
AN AXIAL DIRECTION. J. L. Allen and Andrew 
Beke. January 1953. 27p. diagrs., photos., tab. 
(NACA RM E52K14) 



INVESTIGATION AT SUPERSONIC SPEEDS OF AN 
INLET EMPLOYING CONICAL FLOW SEPARATION 
FROM A PROBE AHEAD OF A BLUNT BODY. 
Donald P. Hearth and Gerald C. Gorton. January 
1953. 32p. diagrs., photos., tab. 
(NACA RM E52K18) 



A PRELIMINARY INVESTIGATION AT MACH NUM- 
BER 1.91 OF AN INLET CONFIGURATION DESIGNED 
FOR INSENSHTVITY TO POSITIVE ANGLE-OF- 
ATTACK OPERATION. Milton A. Beheim. Julv 
1953. 18p. diagrs., photos. (NACA RM E53E20) 



INVESTIGATION OF A TRANSLATING -CONE INLET 
AT MACH NUMBERS FROM 1.5 TO 2.0. L. Abbott 
Leissler and William H. Sterbentz. May 1954. 29p. 
diagrs., photos., tab. (NACA RM E54B23) 



INVESTIGATION OF A FLOW DEFLECTOR AND AN 
AUXILIARY SCOOP FOR IMPROVING OFF-DESIGN 

PERFORMANCE OF NOSE INLETS. Warren E. 
Anderson and Richard Scherrer, July 1954. 32p. 
diagrs., photos. (NACA RM A54E06) 



FLIGHT DETERMINATION OF THE DRAG OF 
CONICAL-SHOCK NOSE INLETS WITH VARIOUS 
COWLING SHAPES AND AXIAL POSITIONS OF THE 
CENTER BODY AT MACH NUMBERS FROM 0.8 TO 
2.0. Charles F. Merlet and Leonard W. Putland. 
September 1954. 41p. diagrs., photos., tabs. 
(NACA RM L54G21a) 



A STUDY OF SEVERAL THEORETICAL METHODS 
FOR COMPUTING THE ZERO-LIFT WAVE DRAG 
OF A FAMILY OF OPEN-NOSED BODIES OF REVO- 
LUTION IN THE MACH NUMBER RANGE OF 2.0 TO 
4.0. Leroy L. Presley and Emmet A. Mossman. 
September 1958. 61p. diagrs, (NACA TN 4368) 



(1.3.4.2) 
TAIL SHAPE 



EXPERIMENTAL EFFECTS OF PROPULSIVE JETS 
AND AFTERBODY CONFIGURATIONS ON THE 
ZERO-LIFT DRAG OF BODIES OF REVOLUTION AT 
A MACH NUMBER OF 1.59. Carlos A. de Moraes 
andAlbinM. Nowitzky. April 1954. 32p. diagrs., 
photos. (NACARM L54C16) 



TRANSONIC FLIGHT TEST OF A ROCKET- 
POWERED MODEL TO DETERMINE PROPULSIVE 
JET INFLUENCE ON THE CONFIGURATION DRAG. 
Carlos A. deMoraes. June 1954. 16p. diagrs., 
photo. (NACA RM L54D27) 



A FREE -FLIGHT INVESTIGATION OF THE EFFECTS 
OF SIMULATED SONIC TURBOJET EXHAUST ON 
THE DRAG OF A BOATTAIL BODY WITH VARIOUS 
JET SIZES FROM MACH NUMBER 0.87 TO 1.50. 
Ralph A. Falanga. August 1955. 23p. diagrs., 
photos., tab. (NACA RM L55F09a) 



INITIAL INCLINATION OF THE MDONG BOUNDARY 

SEPARATING AN EXHAUSTING SUPERSONIC JET 
FROM A SUPERSONIC AMBIENT STREAM. 
Eugene S. Love. January 1956. 30p. diagrs. 
(NACA RM L55J14) 



78 



( 1 ) AERODYNAMICS 



A FREE-FLIGHT INVESTIGATION OF THE EF- 
FECTS OF A SONIC JET ON THE TOTAL-DRAG 
AND BASE-PRESSURE COEFFICIENTS OF A BOAT- 
TAIL BODY OF REVOLUTION FROM MACH NUM- 
BER 0.83 TO 1.70. Ralph A. Falanga. March 1956. 
18p. diagrs., photo., tab. (NACA RM L55L2D 



TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF A HEATED PROPULSIVE JET 
ON THE PRESSURE DISTRIBUTION ALONG A 
FUSELAGE OVERHANG. Elden S. Cornette and 
Donald H. Ward. April 1956. 42p. diagrs., photos. 
tab. (NACA RM L56A27) 



EFFECTS OF EXTERNAL STREAM FLOW AND 
AFTERBODY VARIATIONS ON THE PERFORMANCE 
OF A PLUG NOZZLE AT HIGH SUBSONIC SPEEDS. 
R. J. Salmi and E. M. Cortright, Jr. October 1956. 
19p. diagrs. (NACA RM E56F1U) 



FREE-FLIGHT INVESTIGATION AT TRANSONIC 
SPEEDS OF DRAG COEFFICIENTS OF A BOATTAIL 
BODY OF REVOLUTION WITH A SIMULATED TUR- 
BOJET EXHAUST ISSUING AT THE BASE FROM 
CONICAL SHORT-LENGTH EJECTORS. Ralph A. 
Falanga and Abraham Leiss. December 1956. 34p. 
diagrs., photos., tab. (NACA RM L56H23) 



(1.3.4.3) 
SIDE INLETS 



EXPERIMENTAL INVESTIGATION AT SUPERSONIC 
SPEEDS OF SIDE SCOOPS EMPLOYING BOUNDARY- 
LAYER SUCTION. Sherman S. Edwards. 
December 12, 1949. 37p. diagrs., photos. 
(NACA RM A9I29) 



ANALYTICAL AND EXPERIMENTAL INVESTIGA- 
TION OF INLET-ENGINE MATCHING FOR 
TURBOJET-POWERED AIRCRAFT AT MACH NUM- 
BERS UP TO 2.0. Carl F. Schueller and Fred T. 
Esenwein. February 1952. 31p. diagrs., photos. 
(NACA RM E51K20) 



PERFORMANCE CHARACTERISTICS AT MACH 
NUMBERS TO 2.0 OF VARIOUS TYPES OF SIDE IN- 
LETS MOUNTED ON FUSELAGE OF PROPOSED 
SUPERSONIC AIRPLANE. I - TWO-DIMENSIONAL 
COMPRESSION-RAMP INLETS WITH SEMICIRCU- 
LAR COWLS. Alfred S. Valerino. July 1952. 43p. 
diagrs., photos., tab. (NACA RM E52E02) 



PERFORMANCE CHARACTERISTICS AT MACH 
NUMBERS TO 2.0 OF VARIOUS TYPES OF SIDE 
INLETS MOUNTED ON FUSELAGE OF PROPOSED 
SUPERSONIC AIRPLANE, n - INLETS UTILIZING 
HALF OF A CONICAL SPIKE. J. L. Allen and 
P. C. Simon. September 1952. 49p. diagrs., 
photos., tab. (NACA RM E52G08) 



PERFORMANCE CHARACTERISTICS AT MACH 
NUMBERS TO 2.00 OF VARIOUS TYPES OF SIDE 
INLETS MOUNTED ON FUSELAGE OF PROPOSED 
SUPERSONIC AIRPLANE, m - NORMAL-WEDGE 
INLET WITH SEMICIRCULAR COWL. Fred T. 
Esenwein. October 1952. 43p. diagrs., photos. 
(NACA RM E52H20) 



PERFORMANCE CHARACTERISTICS AT MACH 
NUMBERS TO 2.0 OF VARIOUS TYPES OF SIDE 
INLETS MOUNTED ON FUSELAGE OF PROPOSED 
SUPERSONIC AIRPLANE. IV - RECTANGULAR- 
COWL INLETS WITH TWO-DIMENSIONAL COM- 
PRESSION RAMPS. Paul C. Simon. October 1952. 
35p. diagrs., photos. (NACA RM E52H29) 



INVESTIGATION AT TRANSONIC SPEEDS OF A 
FORWARD-LOCATED UNDERSLUNG AIR INLET 
ON A BODY OF REVOLUTION. P . Kenneth 
Pierpont and John A. Braden. January 1953. 
109p. diagrs., photos., tabs. (NACA RM L52K17) 



EFFECT OF CIRCUMFERENTIAL LOCATION ON 
ANGLE OF ATTACK PERFORMANCE OF TWIN 
HALF-CONICAL SCOOP-TYPE INLETS MOUNTED 
SYMMETRICALLY ON THE RM-10 BODY OF REV- 
OLUTION. Alfreds. Valerino, Donald B. 
Pennington, and Donald J. Vargo. September 1953. 
37p. diagrs., photos. (NACA RM E53G09) 



PRESSURE RECOVERY AND DRAG CHARACTERIS- 
TICS OF A FORWARD LOCATED CIRCULAR SCOOP 
INLET AS DETERMINED FROM FLIGHT TESTS FOR 
MACH NUMBERS FROM 0.8 TO 1.6. Charles F. 
Merlet. April 1954. 23p. diagrs., photos., tab. 
(NACA RM L54B23) 



FLIGHT DETERMINATION OF DRAG AND PRES- 
SURE RECOVERY OF TWO SCOOP INLETS LO- 
CATED AT MAXIMUM-BODY-DIAMETER STATION 
AT MACH NUMBERS FROM 0.8 TO 1.8. Leonard 
W. Putland. January 1956. 24p. diagrs., photos., 
tab. (NACA RM L55H22a) 



CRITERIA FOR INITIAL FLOW REVERSAL IN 
SYMMETRICAL TWIN-INTAKE AIR-INDUCTION 
SYSTEMS OPERATING AT SUPERSONIC SPEEDS. 
Andrew Beke. February 1956. 17p. diagrs. 
(NACA RM E55L02a) 



EFFECT OF FUSELAGE CIRCUMFERENTIAL 
INLET LOCATION ON DIFFUSER- DISCHARGE 
TOTAL-PRESSURE PROFD^ES AT SUPERSONIC 
SPEEDS. Emil J. Kremzier and Joseph F. 
Wasserbauer. October 1956. 14p. diagrs. 
(NACA RM E56G26) 



EFFECT OF WALL COOLING ON INLET PARAME- 
TERS OF A SCOOP OPERATING IN A TURBULENT 
BOUNDARY LAYER ON A FLAT OR CONICAL SUR- 
FACE FOR MACH NUMBERS 2 TO 10. Andrew Beke. 
March 1958. 21p. diagrs., tabs. 
(NACA TN 4153) 



79 



( 1 ) AERODYNAMICS 



(1. 3.4.4) 
SIDE EXITS 



SUMMARY OF SCALE-MODEL THRUST -REVERSER 
INVESTIGATION. John H. Povolny, Fred W. Stefff 
and Jack G. McArdle. 1957. it, I4p. diagrs., 
photos. (NACA Rept. 1314. Supersedes TN 3664) 



AN INVESTIGATION OF DISCHARGE AND THRUST 
CHARACTERISTICS OF FLAPPED OUTLETS FOR 
STREAM MACH NUMBERS FROM 0.40 TO 1,30. 

Allen R. Vick. July 1957. 47p. diagrs. 
(NACA TN 4007) 



80 



(1) AERODYNAMICS 



(1-4) 
Internal Aerodynamics 



PERFORMANCE CHARACTERISTICS AT MACH 
NUMBERS TO 2.0 OF VARIOUS TYPES OF SIDE 
INLETS MOUNTED ON FUSELAGE OF PROPOSED 
SUPERSONIC AIRPLANE. IV - RECTANGULAR- 
COWL INLETS WITH TWO-DIMENSIONAL COM- 
PRESSION RAMPS p'sujl C- Si^on October 19*2 
35p. diagrs., photos. (NACA RM E52H29) 



PERFORMANCE OF A SWEPT LEADING EDGE 
ROTOR OF THE SUPERSONIC TYPE WITH MDCED 
FLOW. Arthur W. Goldstein and Ralph L. Schacht. 
January 1953. 34p . diagrs., photo., tab. 
(NACA RM E52K03) 



ALTITUDE STARTING CHARACTERISTICS OF AN 
AFTERBURNER WITH AUTOKJNTriON AND HOT- 
STREAK IGNITION. P. E. Renas, R. W. Harvey, 
Sr., and E. T. Jansen, April 1953. 25p. diagrs., 
photos., tab. (NACARME53B02) 



PERFORMANCE OF A SUPERSONIC MIXED-FLOW 
ROTOR WITH A SWEPT LEADING EDGE AND 0.52 
INLET RADIUS RATIO. Arthur W. Goldstein and 
Ralph L. Schacht. November 1953. 34p. diagrs., 
photos., tab. (NACA RM E53H27) 



ATTENUATION IN A SHOCK TUBE DUE TO 
UNSTEADY-BOUNDARY-LAYER ACTION. Harold 
Mirels. 1957. iii, 19p. diagrs., tab. 
(NACARept. 1333. Supersedes TN 3278) 



ANALYSIS OF SHOCK MOTION IN DUCTS DURING 
DISTURBANCES IN DOWNSTREAM PRESSURE. 
Herbert G. Hurrell. September 1957. lip. diagr. 
(NACA TN 4090) 



FLOW-TURNING LOSSES ASSOCIATED WITH ZERO- 
DRAG EXTERNAL -COMPRESSION SUPERSONIC 
INLETS. Rudolph C. Meyer. October 1957. 18p. 
diagrs. (NACA TN 4096) 



(1.4.1) 
AIR INLETS 



TRANSONIC FLIGHT TESTS TO DETERMINE ZERO- 
LIFT DRAG AND PRESSURE RECOVERY OF NA- 
CELLES LOCATED AT THE WING ROOT ON A 45° 
SWEPTBACK WING AND BODY CONFIGURATION. 
Sherwood Hoffman and Austin L. Wolff. September 
1953. 31p. diagrs., photos., tabs. 
(NACARM L53H20) 



AN ANALYSIS OF THE TRANSONIC AND SUPER- 
SONIC PERFORMANCE OF SEVERAL FDCED- 
GEOMETRY AIR INLETS - Robert E . Pendley and 
Robert R. Howell. March 1955. 36p diagrs., 
tab. (NACA RM L54L29) 



EFFECT OF FUSELAGE CIRCUMFERENTIAL 
INLET LOCATION ON DIFF USER -DISCHARGE 
TOTAL-PRESSURE PROFILES AT SUPERSONIC 
SPEEDS. Emil J. Kremzier and Joseph F. 
Wasserbauer. October 1956. 14p. diagrs. 
'NACA RM ESS^S 1 * 



FOREIGN-OBJECT RETENTION AND FLOW CHAR- 
ACTERISTICS OF RETRACTABLE ENGINE-INLET 
SCREENS. Fred W. Steffen and Lewis A. Rodert. 
July 1957. 30p. diagrs., photos. 
(NACA RM E57A15) 



ANALYSIS OF SHOCK MOTION IN DUCTS DURING 
DISTURBANCES IN DOWNSTREAM PRESSURE. 
Herbert G. Hurrell. September 1957. lip. diagr. 
(NACA TN 4090) 



EXPERIMENTAL INVESTIGATION OF THE EF- 
FECTS OF SOME SHROUD DESIGN VARIABLES ON 
THE STATIC THRUST CHARACTERISTICS OF A 
SMALL-SCALE SHROUDED PROPELLER SUB- 
MERGED IN A WING. Robert T. Taylor. January 
1958. 23p. diagrs., photos. (NACA TN 4126) 



DROPLET IMPINGEMENT AND INGESTION BY 
SUPERSONIC NOSE INLET IN SUBSONIC TUNNEL 
CONDITIONS. Thomas F. Gelder. May 1958. 56p. 
diagrs., photos. (NACA TN 4268) 



A PERFORMANCE ANALYSIS OF METHODS FOR 
HANDLING EXCESS INLET FLOW AT SUPERSONIC 
SPEEDS. Donald P. Hearth and James F. Connors. 
May 1958. 26p. diagrs., tab. (NACA TN 4270) 



(1.4.1.1) 

NOSE, CENTRAL 



NACA INVESTIGATIONS OF ICING-PROTECTION 
SYSTEMS FOR TURBOJET-ENGINE INSTALLA- 
TIONS. Uwe von Glahn, Edmund E. Callaghan, and 
Vernon H. Gray. May 2, 1951. (ii), 83p. diagrs., 
photoa. (NACA RM E51B12) 



PERFORMANCE CHARACTERISTICS OF CANARD- 
TYPE MISSILE ATTH VERTICALLY MOUNTED 
NACELLE ENGINES AT MACH NUMBERS 1.5 TO 
2.0. Leonard J. Obery and Howard S. Krasnow. 
September 1952. 25p. diagrs. (NACA RM E52H08) 



PERFORMANCE CHARACTERISTICS OF CANARD- 
TYPE MISSILE WITH WING-MOUNTED NACELLE 
ENGINES AT MACH NUMBERS 1.5 TO 2.0. EmU J. 
Kremzier and Joseph Davids. November 1952. 
30p. diagrs., tab. (NACA RM E52J08) 



81 



(1) AERODYNAMICS 



THE EFFECT OF INITIAL RATE OF SUBSONIC 
DIFFUSION ON THE STABLE SUBCRITICAL MASS- 
FLOW RANGE OF A CONICAL SHOCK DIFFUSER. 
J. C. Nettles. July 1953. 23p. diagrs. 
(NACA RM E53E26) 



AN ANALYTICAL STUDY OF THE COMPARATIVE 
PERFORMANCE OF SDC AIR-INDUCTION SYSTEMS 
FOR TURBOJET-POWERED AIRPLANES DESIGNED 
TO OPERATE AT MACH NUMBERS UP TO 2.0. 
Earl C. Watson. October 1953. 46p. diagrs. 
(NACA RM A53H03) 



INVESTIGATION OF A FLOW DEFLECTOR AND AN 
AUXILIARY SCOOP FOR IMPROVING OFF-DESIGN 
PERFORMANCE OF NOSE INLETS. Warren E. 
Anderson and Richard Scherrer. July 1954. 32p. 
diagrs., photos. (NACA RM A54E06) 



(1.4.1. 1. 1) 

Propeller -Spinner -Cowl 
Combinations 



AN INVESTIGATION OF SINGLE- AND DUAL- 
ROTATION PROPELLERS AT POSITIVE AND 
NEGATIVE THRUST, AND IN COMBINATION WITH 
AN NACA 1 -SERIES D-TYPE COWLING AT MACH 

NUMBERS UP TO 0.84. Robert M. Reynolds, 
Robert I. Sammonds, and John H. Walker. 1957. 
ii, 58p. diagrs., photos., tabs. (NACA Rept. 1336) 



INVESTIGATION OF HEAT TRANSFER FROM A 
STATIONARY AND ROTATING CONICAL FORE- 
BODY. Roberts. Ruggeri and James P . Lewis. 
October 1957. 30p. diagrs., photo., tab. 
(NACA TN 4093) 



EXPERIMENTAL DROPLET IMPINGEMENT ON 
FOUR BODIES OF REVOLUTION. James P. Lewis 
and Robert S. Ruggeri. December 1957. 61p. 
diagrs. , photos. (NACA TN 4092) 



(1.4.1.1.2) 

Subsonic 



INVESTIGATION OF TRANSLA TING-SPIKE SUPER- 
SONIC INLET AS MEANS OF MASS -FLOW CONTROL 
AT MACH NUMBERS OF 1.5, 1.8, AND 2.0. Gerald 
C. Gorton. October 1953. 23p. diagrs., photos., 
tabs. (NACA RM E53G10) 



SOME CONSIDERATIONS CONCERNING INLETS 
AND DUCTED BODIES AT MACH NUMBERS FROM 
0.8 TO 2.0. Richard I. Sears. November 1953. 
17p. diagrs. (NACA RM L53l25b) 



A METHOD FOR DESIGNING LOW-DRAG NOSE- 
INLET-BODY COMBINATIONS FOR OPERATION 
AT MODERATE SUPERSONIC SPEEDS. Robert R. 
Howell. November 1954. 29p. diagrs., photos., 
tab. (NACA RM L54I01a) 



TURBULENT FLOW THROUGH POROUS RESIST- 
ANCES SLIGHTLY INCLINED TO THE FLOW 
DIRECTION. Albert L. Loeffler, Jr., and Morris 
Perlmutter. February 1958. 30p. diagrs., photos. 
(NACA TN 4221) 



(1,4.1. 1.3) 
Supersonic 



FORCE AND PRESSURE CHARACTERISTICS FOR A 
SERIES OF NOSE INLETS AT MACH NUMBERS 
FROM 1.59 TO 1.99. I - CONICAL SPIKE ALL- 
EXTERNAL COMPRESSION INLET WITH SUBSONIC 
COWL LD?. Fred T. Esenwein and Alfred S. 
Valerlno. January 19, 1951. 73p. diagrs., photos., 
tabs. (NACA RM E50J26) 



FORCE AND PRESSURE CHARACTERISTICS FOR A 
SERIES OF NOSE INLETS AT MACH NUMBERS 
FROM 1.59 TO 1.99. H - ISENTROPIC-SPIKE ALL- 
EXTERNAL COMPRESSION INLET. L. J. Obery 
andG. W. Englert. February 9, 1951. 67p. 
diagrs., photos., tabs. (NACA RM E50J26a) 



FORCE AND PRESSURE CHARACTERISTICS FOR A 
SERIES OF NOSE INLETS AT MACH NUMBERS 
FROM 1.59 TO 1.99. Ill - CONICAL-SPIKE ALL- 
EXTERNAL-COMPRESSION INLET WITH SUPER- 
SONIC COWL LIP. Maynard I. Weinstein and Joseph 
Davids. February 14, 1951. 51p. diagrs., tabs. 
(NACA RM E50J30) 



FORCE AND PRESSURE CHARACTERISTICS FOR A 
SERIES OF NOSE INLETS AT MACH NUMBERS 
FROM 1.59 TO 1.99. IV - CONICAL-SPIKE 
EXTERNAL-INTERNAL COMPRESSION INLET 
UTILIZING PERFORATED COWL. Robert T. 
Madden and Emil J. Kremzier. March 28, 1951. 
46p. diagrs., photos., tabs. (NACA RM E51B05) 



PRELIMINARY INVESTIGATION OF EFFECT OF 
ANGLE OF ATTACK ON PRESSURE RECOVERY 
AND STABILITY CHARACTERISTICS FOR A 
VERTICAL-WEDGE-NOSE INLET AT MACH NUM- 
BER OF 1 90. L. Abbott Leissler and Donald P. 
Hearth. August 1952. lip. diagrs., photos. 
(NACA RM E52E14) 



PERFORMANCE CHARACTERISTICS OF CANARD- 
TYPE MISSILE vVITH VERTICALLY MOUNTED 
NACELLE ENGINES AT MACH NUMBERS 1.5 TO 
2.0. Leonard J. Obery and Howard S. Krasnow. 
September 1952. 25p. diagrs. (NACA RM E52H08) 



PERFORMANCE CHARACTERISTICS OF CANARD- 
TYPE MISSILE WITH WING-MOUNTED NACELLE 
ENGINES AT MACH NUMBERS 1.5 TO 2.0. Emil J. 
Kremzier and Joseph Davids. November 1952. 
30p. diagrs., tab. (NACA RM E52J08) 



PRELIMINARY INVESTIGATION OF THE EFFECTS 
OF INLET ASYMMETRY ON THE PERFORMANCE 
OF CONVERGING -DIVERGING DIFFUSERS AT 

TRANSONIC SPEEDS. John S. Dennard and William 
J. Nelson. November 1952. 30p. diagrs., photos., 
tab. (NACARM L52J20) 



INVESTIGATION AT SUPERSONIC SPEEDS OF AN 
INLET EMPLOYING CONICAL FLOW SEPARATION 
FROM A PROBE AHEAD OF A BLUNT BODY. 
Donald P. Hearth and Gerald C, Gorton. January 
1953. 32p. diagrs., photos., tab. 
(NACA RM E52K18) 



82 



(1) AERODYNAMICS 



INVESTIGATION OF PRESSURE RECOVERY OF A 
SINGLE -CONICAL -SHOCK NOSE INLET AT MACH 
NLMBER 5.4. Harry Bernstein and Rudolph C. 
Haefeli. April 1953. 22p. diagrs., photos. 

(NACA RM E53A12) 



A PRELIMINARY INVESTIGATION AT MACH NUM- 
BER 1.91 OF AN INLET CONFIGURATION DESIGNED 
FOR INSENSITIVITY TO POSITIVE ANGLE-OF- 
ATTACK OPERATION. Milton A. Beheim. July 
1953. 18p. diagrs., photos. (NACA RM E53E20) 



THE EFFECT OF INITIAL RATE OF SUBSONIC 
DIFFUSION ON THE STABLE SUBCRITICAL MASS- 
FLOW RANGE OF A CONICAL SHOCK DIFFUSER. 
J. C. Nettles. July 1953. 23p. diagrs. 
(NACA RM E53E26) 



SOME CONSIDERATIONS CONCERNING INLETS 
AND DUCTED BODIES AT MACH NUMBERS FROM 
0.8 TO 2.0. Richard I. Sears. November 1953. 
17p. diagrs. (NACA RM L53I25b) 



PRELIMINARY INVESTIGATION OF THE TOTAL- 
PRESSURE -RECOVERY CHARACTERISTICS OF A 
SYMMETRIC AND AN ASYMMETRIC NOSE INLET 
OVER A WIDE RANGE OF ANGLE OF ATTACK AT 
SUPERSONIC MACH NUMBERS. Howards. Carter 
and Charles F. Merlet. December 1953. 27p. 
diagrs., photo. (NACA RM L53J30) 



INVESTIGATION OF A FLOW DEFLECTOR AND AN 
AUXILIARY SCOOP FOR IMPROVING OFF-DESIGN 
PERFORMANCE OF NOSE INLETS. Warren E. 
Anderson and Richard Scherrer. July 1954. 32p. 
diagrs., photos. (NACA RM A54E06) 



A METHOD FOR DESIGNING LOW-DRAG NOSE- 
INLET-BODY COMBINATIONS FOR OPERATION 
AT MODERATE SUPERSONIC SPEEDS. Robert R. 
Howell. November 1954. 29p. diagrs., photos., 
tab. (NACA RM L 5410 la) 



INVESTIGATION TO MACH NUMBER 2.0 OF SHOCK - 
POSITIONING CONTROL SYSTEMS FOR A 
VARIABLE-GEOMETRY INLET IN COMBINATION 
WITH A J34 TURBOJET ENGINE. L. Abbott 
Leissler and J. Cary Nettles. December 1954. 19p. 
diagrs. (NACA RM E54I27) 



AERODYNAMIC CHARACTERISTICS AT MACH NUM- 
BERS FROM 0.7 TO 1.75 OF A FOUR-ENGINE 
SWEPT-WING AIRPLANE CONFIGURATION AS 
OBTAINED FROM A ROCKET-PROPELLED MODEL 
TEST. Rowe Chapman, Jr. September 1955. 39p. 
diagrs., photos., tabs. (NACA RM L55F23) 



FLIGHT INVESTIGATION OF A RAM JET BURNING 
MAGNESIUM SLURRY FUEL AND HAVING A CONI- 
CAL SHOCK INLET DESIGNED FOR A MACH NUM- 
BER OF 4.1. Walter A. Bartlett, Jr., and 
Charles F. Merlet. January 1957. 23p. diagrs., 
photos. (NACA RM L56I24a) 



A PRELIMINARY INVESTIGATION OF METHODS 
FOR IMPROVING THE PRESSURE -RECOVERY 
CHARACTERISTICS OF VARIABLE -GEOMETRY 
SUPERSONIC-SUBSONIC DIFFUSER SYSTEMS. 
Lowell E. Hasel and Archibald R. Sinclair. October 
1957. 57p. diagrs., photos. (NACA RM L57H02) 



(1.4.1.2) 
NOSE, ANNULAR 



FORCE AND PRESSURE CHARACTERISTICS FOR A 
SERIES OF NOSE INLETS AT MACH NUMBERS 
FROM 1.59 TO 1.99. I - CONICAL SPIKE ALL- 
EXTERNAL COMPRESSION INLET WITH SUBSONIC 
COWL LIP. Fred T. Esenweln and Alfred S. 
Valerino. January 19, 1951. 73p. diagrs., photos., 
tabs. (NACA RM E50J26) 



FORCE AND PRESSURE CHARACTERISTICS FOR A 
SERIES OF NOSE INLETS AT MACH NUMBERS 
FROM 1.59 TO 1.99. H - ISENTROPIC -SPIKE ALL- 
EXTERNAL COMPRESSION INLET. L.J. Obery 
and G. W. Englert. February 9, 1951. 67p. 
diagrs., photos., tabs. (NACA RM E50J26a) 



FORCE AND PRESSURE CHARACTERISTICS FOR A 
SERIES OF NOSE INLETS AT MACH NUMBERS 
FROM 1.59 TO 1.99. Ill - CONICAL -SPIKE ALL- 
EXTERNAL-COMPRESSION INLET WITH SUPER- 
SONIC COWL LB?. Maynard I. Weinstein and Joseph 
Davids. February 14, 1951. 51p. diagrs., tabs. 
(NACA RM E50J30) 



FORCE AND PRESSURE CHARACTERISTICS FOR A 
SERIES OF NOSE INLETS AT MACH NUMBERS 
FROM 1.59 TO 1.99. IV - CONICAL -SPIKE 
EXTERNAL-INTERNAL COMPRESSION INLET 
UTDLIZING PERFORATED COWL. Robert T. 
Madden and Emil J. Kremzier. March 28, 1951. 
46p. diagrs., photos., tabs. (NACA RM E51B05) 



EVALUATION OF FIVE CONICAL CENTER-BODY 
SUPERSONIC DIFFUSERS AT SEVERAL ANGLES OF 
ATTACK. Gerald W. Englert and Leonard J. Obery. 
May 1952. 29p. diagrs., photos., tab. 
(NACARME51L04) 



PRELIMINARY INVESTIGATION OF EFFECT OF 
ANGLE OF ATTACK ON PRESSURE RECOVERY 
AND STABILITY CHARACTERISTICS FOR A 
VERTICAL-WEDGE-NOSE INLET AT MACH NUM- 
BER OF 1.90. L. Abbott Leissler and Donald P. 
Hearth. August 1952. lip. diagrs., photos. 
(NACA RM E52E14) 



FORCE AND PRESSURE RECOVERY CHARACTER- 
ISTICS AT SUPERSONIC SPEEDS OF A CONICAL 
SPIKE INLET WITH BYPASSES DISCHARGING IN 
AN AXIAL DIRECTION. J. L, Allen and Andrew 
Beke. January 1953. 27p. diagrs., photos., tab. 
(NACA RM E52K14) 



INVESTIGATION AT SUPERSONIC SPEEDS OF AN 
INLET EMPLOYING CONICAL FLOW SEPARATION 
FROM A PROBE AHEAD OF A BLUNT BODY. 
Donald P. Hearth and Gerald C. Gorton. January 
1953. 32p. diagrs., photos., tab. 
(NACA RM E52K18) 



A PRELIMINARY INVESTIGATION AT MACH NUM- 
BER 1.91 OF AN INLET CONFIGURATION DESIGNED 
FOR INSENSITIVrTY TO POSITIVE ANGLE-OF- 
ATTACK OPERATION. Milton A. Beheim. July 
1953. 18p. diagrs., photos. (NACA RM E53E20) 



83 



(1) AERODYNAMICS 



THE EFFECT OF INITIAL RATE OF SUBSONIC 
DIFFUSION ON THE STABLE SUBCRITICAL MASS- 
FLOW RANGE OF A CONICAL SHOCK DIFFUSER. 
J- C. Nettles. July 1953. 23p. diagrs - 
(NACA RM E53E26) 



INVESTIGATION OF TRANS LA TING -SPIKE SUPEH- 
SONIC INLET AS MEANS OF MASS-FLOW CONTROL 
AT MACH NUMBERS OF 1.5, 1.8, AND 2.0. Gerald 
C. Gortori. October 1953. 23p, diagrs., photos., 
tabs. (NACA RM E53G10) 



SOME CONSIDERATIONS CONCERNING INLETS 
AND DUCTED BODIES AT MACH NUMBERS FROM 
0.8 TO 2.0. Richard I. Sears. November 1953. 
1 7p . diagrs . (NACA RM L53I2 5b) 



INVESTIGATION OF A TRANSLATING -CONE INLET 
AT MACH NUMBERS FROM 1.5 TO 2.0. L. Abbott 
Leissler and William H. Sterbentz. May 1954. 29p, 
diagr s., photos., tab. (NACA RM E54B23) 



FLIGHT DETERMINATION OF THE DRAG OF 
CONICAL-SHOCK NOSE INLETS WITH VARIOUS 
COWLING SHAPES AND AXIAL POSITIONS OF THE 
CENTER BODY AT MACH NUMBERS FROM 0.8 TO 
2.0. Charles F. Merlet and Leonard W. Putland. 
September 1954. 41p. diagrs., photos., tabs. 
(NACA RM L54G21a) 



DRAG DATA FOR 16-INCH-DIAMETER RAM-JET 
ENGINE WITH DOUBLE-CONE INLET IN FREE 
FLIGHT AT MACH NUMBERS FROM 0.7 TO 1.8. 
Merle L. Jones, Leonard Rabb, and Scott H. 
Simpkinson. October 1954. 52p. diagrs., photos. 
(NACA RM E54H02) 



A VARIABLE -GEOMETRY AXISYMMETRIC SUPER- 
SONIC INLET WITH TELESCOPING CENTERBODY. 
James F. Connors and Rudolph C. Meyer. 
September 1955. 27p. diagrs., photos., tabs. 
(NACA RM E55F30) 



(1.4.1.3) 

WING LEADING EDGE 



SOME OBSERVATIONS OF FLOW AT THE THROAT 
OF A TWO-DIMENSIONAL DIFFUSER AT THE 
MACH NUMBER OF 3.85. James F. Connors and 
Richard R. Woollett. November 1952. 13p. photos., 
diagrs. (NACA RM E52I04) 



SOME CONSIDERATIONS CONCERNING INLETS 
AND DUCTED BODIES AT MACH NUMBERS FROM 
0.8 TO 2.0. Richard I. Sears. November 1953. 
17p. diagrs. (NACA RM L53I25b) 



INVESTIGATION AT TRANSONIC SPEEDS OF AERO- 
DYNAMIC CHARACTERISTICS OF A SEMIELLTPTI- 
CAL ATR INLET IN THE ROOT OF A 45° SWEPT- 
BACK WING. Robert R. Howell and Charles D. 
Trescot, Jr. December 1953. 39p. diagrs., 
photos., tabs. (NACA RM L53j22a) 



TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF BODY INDENTATION ON THE 
AERODYNAMIC CHARACTERISTICS OF A SEMI- 
ELLIPTICAL SWEPTBACK WING-ROOT INLET 
CONFIGURATION. Arvid L. Keith, Jr. March 
1954. 22p. diagrs., photos., tabs. 
(NACA RM L54A29) 



AN EXPERIMENTAL INVESTIGATION OF TWO- 
DIMENSIONAL, SUPERSONIC CASCADE-TYPE 
INLETS AT A MACH NUMBER OF 3.11. Edward 
Offenhartz. August 1954. 29p. diagrs., photos. 
(NACA RM L54E17) 



PRELIMINARY INVESTIGATION AT MACH 
NUMBER 1.9 OF SIMULATED WING-ROOT INLETS. 
Thomas G. Piercy and Maynard I. Weinstein. 
January 1955. 60p. diagrs., photos., tab. 
(NACA RM E54I24) 



INVESTIGATION AT TRANSONIC SPEEDS OF AERO- 
DYNAMIC CHARACTERISTICS OF A SEMICIRCULAR 
AIR INLET IN THE ROOT OF A 45<> SWEPTBACK 

WING. Charles D. Trescot, Jr., and Arvid L. 
Keith, Jr. March 1955. 30p. diagrs., photos., tab. 
(NACARM L55A05a) 



INVESTIGATION AT TRANSONIC SPEEDS OF AERO- 
DYNAMIC CHARACTERISTICS OF AN UNSWEPT 
SEMIELL1PTICAL AIR INLET IN THE ROOT OF A 
45° SWEPTBACK WING. Gene J. Bingham. 
September 1955. 37p. diagrs., photos., tabs. 
(NACA RM L55F22a) 



THE EFFECT OF INLET INSTALLATION ON THE 
ZERO-LIFT DRAG OF A 60° DELTA-WING-BODY 
CONFIGURATION FROM FLIGHT TESTS AT MACH 
NUMBERS FROM 0.8 TO 1.86. Charles F. Merlet. 
December 1955. 29p. diagrs., photos., tabs. 
(NACA RM L55I09) 



INVESTIGATION AT TRANSONIC SPEEDS OF THE 
EFFECTS OF INLET LIP STAGGER ON THE 
INTERNAL-FLOW CHARACTERISTICS OF AN 
UNSWEPT SEMIELLIPTICAL AIR INLET. Gene J. 
Bingham and Charles D. Trescot, Jr. May 1956. 
31p. diagrs., photos., tab. (NACA RM L56C22) 



(1.4.1.4) 
SIDE 



EXPERIMENTAL INVESTIGATION AT SUPERSONIC 
SPEEDS OF SIDE SCOOPS EMPLOYING BOUNDARY- 
LAYER SUCTION. Sherman S. Edwards. 
December 12, 1949. 37p. diagrs., photos. 
(NACA RM A9I29) 



INVESTIGATION AT MACH NUMBER 1.88 OF HALF 
OF A CONICAL-SPIKE DIFFUSER MOUNTED AS A 
SIDE INLET WITH BOUNDARY- LAYER CONTROL. 
H. Fred Goelzer and Edgar M. Cortright, Jr. 
September 1951. 38p. diagrs., photos. 
(NACARME51G06) 



PERFORMANCE CHARACTERISTICS AT MACH 
NUMBERS TO 2.0 OF VARIOUS TYPES OF SIDE 
INLETS MOUNTED ON FUSELAGE OF PROPOSED 
SUPERSONIC AIRPLANE. II - INLETS UTILIZING 
HALF OF A CONICAL SPIKE. J. L. Allen and 
P. C. Simon. September 1952. 49p. diagrs., 
photos., tab. (NACA RM E52G08) 



INVESTIGATION AT MACH NUMBER 2.93 OF HALF 
OF A CONICAL-SPIKE DIFFUSER MOUNTED AS A 
SIDE INLET WITH BOUNDARY-LAYER CONTROL. 
Thomas G. Piercy and Harry W. Johnson. 
September 1952. 39p. diagrs., photos. 
(NACA RM E52G23) 



84 



(1) AERODYNAMICS 



PERFORMANCE CHARACTERISTICS AT MACH 
NUMBERS TO 2.00 OF VARIOUS TYPES OF SIDE 
INLETS MOUNTED ON FUSELAGE OF PROPOSED 
SUPERSONIC AIRPLANE, m - NORMAL-WEDGE 
INLET WITH SEMICIRCULAR COWL. Fred T. 
E sen we in. October 1952. 43p. diagrs,, photos. 
(NACA RM E52H20) 



PERFORMANCE CHARACTERISTICS AT MACH 
NUMBERS TO 2.0 OF VARIOUS TYPES OF SIDE 
INLETS MOUNTED ON FUSELAGE OF PROPOSED 
SUPERSONIC AIRPLANE. IV - RECTANGULAR- 
COWL INLETS WITH TWO-DIMENSIONAL COM- 
PULSION RAMPS. PaulC. Simon. October 1052. 
35p. diagrs., photos. (NACA RM E52H29) 



A COMPARISON OF SEVERAL SYSTEMS OF 
BOUNDARY-LAYER REMOVAL AHEAD OF A TYPI- 
CAL CONICAL EXTERNAL-COMPRESSION SIDE 
INLET AT MACH NUMBERS OF 1.88 AND 2.93. 
Thomas G. Plercy and Harry W. Johnson. 
September 1953. 58p. diagrs., photos. 
(NACA RM E53F16) 



EFFECT OF CIRCUMFERENTIAL LOCATION ON 
ANGLE OF ATTACK PERFORMANCE OF TWIN 
HALF-CONICAL SCOOP-TYPE INLETS MOUNTED 
SYMMETRICALLY ON THE RM-10 BODY OF REV- 
OLUTION. Alfred S. Valerino, Donald B. 
Pennington, and Donald J. Vargo. September 1953. 
37p. diagrs., photos. (NACA RM E53G09) 



INVESTIGATION AT TRANSONIC SPEEDS OF AERO- 
DYNAMIC CHARACTERISTICS OF AN UNSWEPT 
SEMIELL1PTICAL AIR INLET IN THE ROOT OF A 
450 SWEPTBACK WING. Gene J. Bingham. 
September 1955. 37p. diagrs., photos., tabs. 
(NACA RM L55F22a) 



AN EXPERIMENTAL STUDY OF A METHOD FOR 
DESIGNING FUSELAGE SIDE AIR INLETS FOR HIGH 
PERFORMANCE AT TRANSONIC AND LOW SUPER- 
SONIC SPEEDS. Robert R. Howell and Charles D. 
Trescot, Jr. January 1956. 24p. diagrs., photos., 
tabs. (NACA RM L55G19) 



INVESTIGATION AT TRANSONIC SPEEDS OF THE 
EFFECTS OF INLET LB? STAGGER ON THE 
INTERNAL-FLOW CHARACTERISTICS OF AN 
UNSWEPT SEMIELLIPTICAL AIR INLET. Gene J. 
Bingham and Charles D. Trescot, Jr. May 1956. 
31p. diagrs., photos., tab. (NACA RM L56C22) 



EFFECT OF FUSELAGE CIRCUMFERENTIAL 
INLET LOCATION ON DIFF USER -DISCHARGE 
TOTAL-PRESSURE PROFILES AT SUPERSONIC 
SPEEDS. Emll J. Kremzier and Joseph F. 
Wasserbauer. October 1956. 14p. diagrs. 
(NACA RM E56G26) 



(1.4.1.4. 1) 

Scoops 



EXPERIMENTAL INVESTIGATION AT SUPERSONIC 
SPEEDS OF SIDE SCOOPS EMPLOYING BOUNDARY- 
LAYER SUCTION. Sherman S. Edwards. 
December 12, 1949. 37p. diagrs., photos. 
(NACA RM A9I29) 



INVESTIGATION AT MACH NUMBER 1.88 OF HALF 
OF A CONICAL-SPIKE DIFFUSER MOUNTED AS A 
SIDE INLET WITH BOUNDARY- LAYER CONTROL. 
H. Fred Goelzer and Edgar M. Cortright, Jr. 
September 1951. 38p. diagrs., photos. 
(NACA RM E51G06) 



ANALYTICAL AND EXPERIMENTAL INVESTIGA- 
TION OF INLET-ENGINE MATCHING FOR 
TURBOJET-POWERED AIRCRAFT AT MACH NUM- 
BERS UP TO 2.0. Carl F. Schueller and Fred T. 
Esenwein. February 1952. 31p. diagrs., photos. 
(NACA RM E51K20) 



TOTAL-PRESSURE RECOVERY OF A CIRCULAR 
UNDERSLUNG INLET WITH THREE DIFFERENT 
NOSE SHAPES AT A MMTH NUMBER OF 1.42. 
Charles F. Mer let and Howard S. Carter. February 
1952. 37p. diagrs., photos. (NACA RM L51K05) 



PERFORMANCE CHARACTERISTICS AT MACH 
NUMBERS TO 2.0 Of VARIOUS TYPES OF SIDE IN- 
LETS MOUNTED ON FUSELAGE OF PROPOSED 
SUPERSONIC AIRPLANE. I - TWO-DIMENSIONAL 
COMPRESSION-RAMP INLETS WITH SEMICIRCU- 
LAR COWLS. Alfred S. Valerino. July 1952. 43p. 
diagrs., photos., tab. (NACA RM E52E02) 



INVESTIGATION AT MACH NUMBER 2.93 OF HALF 
OF A CONICAL-SPIKE DIFFUSER MOUNTED AS A 
SIDE INLET WITH BOUNDARY-LAYER CONTROL. 

Thonvis G. Piercy and Harry W. Johnson. 
September 1952. 39p. diagrs., photos. 
(NACA RM E52G23) 



PERFORMANCE CHARACTERISTICS AT MACH 
NUMBERS TO 2.0 OF VARIOUS TYPES OF SIDE 
INLETS MOUNTED ON FUSELAGE OF PROPOSED 
SUPERSONIC AIRPLANE. IV - RECTANGULAR- 
COWL INLETS WITH TWO-DIMENSIONAL COM- 
PRESSION RAMPS. PaulC. Simon. October 1952. 
35p. diagrs., photos. (NACA RM E52H29) 



INVESTIGATION AT TRANSONIC SPEEDS OF A 
FORWARD -LOCATED UNDERSLUNG AIR INLET 
ON A BODY OF REVOLUTION. P. Kenneth 
Pierpont and John A. Braden. January 1953\ 
109p. diagrs., photos., tabs. (NACA RM L52K17) 



INVESTIGATION OF A HALF -CONICAL SCOOP IN- 
LET MOUNTED AT FIVE ALTERNATE CIRCUM- 
FERENTIAL LOCATIONS AROUND A CD3CULAR 
FUSELAGE. PRESSURE-RECOVERY RESULTS AT 
A MACH NUMBER OF 2.01. Lowell E. Hasel, John 
L. Lankford, and A. W. Robins. June 1953. 41p. 
diagrs., photos., tab. (NACA RM L53D30b) 



A COMPARISON OF SEVERAL SYSTEMS OF 
BOUNDARY-LAYER REMOVAL AHEAD OF A TYPI- 
CAL CONICAL EXTERNAL-COMPRESSION SIDE 
INLET AT MACH NUMBERS OF 1.88 AND 2.93. 
Thomas G. Piercy and Harry W. Johnson. 
September 1953. 58p. diagrs., photos. 
(NACA RM E53F16) 



AN ANALYTICAL STUDY OF THE COMPARATIVE 
PERFORMANCE OF SDC AIR-INDUCTION SYSTEMS 
FOR TURBOJET-POWERED AIRPLANES DESIGNED 
TO OPERATE AT MACH NUMBERS UP TO 2.0. 
Earl C. Watson. October 1953. 46p. diagrs. 
(NACA RM A53H03) 



(1) AERODYNAMICS 



85 



SOME CONSIDERATIONS CONCERNING INLETS 
AND DUCTED BODIES ATTACH NUMBERS FROM 
0.8 TO 2.0. Richard I. Sears. November 1953. 
17p. dlagrs. (NACA RM L 531 2 5b) 



PRESSURE RECOVERY AND DRAG CHARACTERIS- 
TICS OF A FORWARD LOCATED CIRCULAR SCOOP 
INLET AS DETERMINED FROM FLIGHT TESTS FOR 
MACH NUMBERS FROM 0.8 TO 1.6. Charles F. 
Merlet. , April 1954. 23p. dlagrs., photos., tab. 
(NACA RM L54B23) 



AN EXPERIMENTAL INVESTIGATION OF TWO- 
DIMENSIONAL, SUPERSONIC CASCADE-TYPE 
INLETS AT A MACH NUMBER OF 3.11. Edward 
Offenhartz. August 1954. 29p. diagrs., photos. 
(NACA RM L54E17) 



PERFORMANCE OF A SUPERSONIC RAMP INLET 
WITH INTERNAL BOUNDARY-LAYER SCOOP. 
Robert C. Campbell. November 1954. 14p. diagrs., 
photo. (NACA RM E54I01) 



MATCHING OF AUXILIARY INLETS TO 
SECONDARY-AIR REQUIREMENTS OF AIRCRAFT 
EJECTOR EXHAUST NOZZLES. Donald P. Hearth, 
Gerald W. Englert, and Kenneth L. Kowalski. 
August 1955. 39p. diagrs. (NACA RM E55D21) 



INVESTIGATION AT TRANSONIC SPEEDS OF AERO- 
DYNAMIC CHARACTERISTICS OF AN UNSWEPT 
SEMIELLIPTICAL AIR INLET IN THE ROOT OF A 
450 SWEPTBACK WING. Gene J. Bingham. 
September 1955, 37p. diagrs., photos., tabs. 
(NACA RM L55F22a) 



A FREE-FLIGHT INVESTIGATION OF THE DRAG 
COEFFICIENTS OF TWO SINGLE-ENGINE SUPER- 
SONIC INTERCEPTOR CONFIGURATIONS FROM 
MACH NUMBER 0.8 TO 1.90 TO DETERMINE THE 
EFFECT OF INLET AND ENGINE LOCATION. 
APPENDDC: SEPARATION CHARACTERISTICS OF 
A MODEL FROM A LARGE UNDERSLUNG BOOSTER 
AT MACH NUMBER 1.95. Joseph H. Judd. 
September 1955. 49p. diagrs., photos., tabs. 
(NACA RM L55G05a) 



THE EFFECT OF INLET INSTALLATION ON THE 
ZERO-LIFT DRAG OF A 60° DELTA-WING-BODY 
CONFIGURATION FROM FLIGHT TESTS AT MACH 
NUMBERS FROM 0.8 TO 1.86. Charles F. Merlet. 
December 1955. 29p. diagrs., photos., tabs. 
(NACA RM L55I09) 



FLIGHT DETERMINATION OF DRAG AND PRES- 
SURE RECOVERY OF TWO SCOOP INLETS LO- 
CATED AT MAXIMUM-BODY-DIAMETER STATION 
AT MACH NUMBERS FROM 0.8 TO 1.8. Leonard 
W. Put land. January 1956. 24p. diagrs., photos., 
tab. (NACA RM L55H22a) 



CRITERIA FOR INITIAL FLOW REVERSAL IN 
SYMMETRICAL TWIN-INTAKE AIR-INDUCTION 
SYSTEMS OPERATING AT SUPERSONIC SPEEDS. 
Andrew Beke. February 1956. 17p. diagrs. 
(NACA RM E55L02a) 



INVESTIGATION AT TRANSONIC SPEEDS OF THE 
EFFECTS OF INLET LIP STAGGER ON THE 
INTERNAL-FLOW CHARACTERISTICS OF AN 
UNSWEPT SEMIELLIPTICAL AIR INLET. Gene J. 
Bingham and Charles D. Trescot, Jr. May 1956. 
31p. diagrs., photos., tab. (NACA RM L56C22) 



EFFECT OF WALL COOLING ON INLET PARAME- 
TERS OF A SCOOP OPERATING IN A TURBULENT 
BOUNDARY LAYER ON A FLAT OR CONICAL SUR- 
FACE FOR MACH NUMBERS 2 TO 10. Andrew Beke. 
March 1958. 21p, diagrs., tabs. 
(NACA TN 4153) 



(1.4.2) 
DUCTS 



PERFORMANCE CHARACTERISTICS AT MACH 
NUMBERS TO 2.0 OF VARIOUS TYPES OF SIDE 
INLETS MOUNTED ON FUSELAGE OF PROPOSED 
SUPERSONIC AIRPLANE. IV - RECTANGULAR- 
COWL INLETS WITH TWO-DIMENSIONAL COM- 
PRESSION RAMPS. PaulC. Simon. October 1952. 
35p. diagrs., photos. (NACA RM E52H29) 



INVESTIGATION AT TRANSONIC SPEEDS OF AERO- 
DYNAMIC CHARACTERISTICS OF A SEMIELLIPTI- 
CAL AIR INLET IN THE ROOT OF A 45<> SWEPT- 
BACK WING. Robert R. Howell and Charles D. 
Trescot, Jr. December 1953. 39p. diagrs., 
photos., tabs. (NACA RM L53J22a) 



TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF BODY INDENTATION ON THE 
AERODYNAMIC CHARACTERISTICS OF A SEMI- 
ELLIPTICAL SWEPTBACK WING-ROOT INLET 
CONFIGURATION. Arvid L. Keith, Jr. March 
1954. 22p. diagrs., photos., tabs. 
(NACA RM L54A29) 



DESIGN AND EVALUATION OF A TURBOJET 
EXHAUST SIMULATOR, UTILIZING A SOLID- 
PROPELLANT ROCKET MOTOR, FOR USE IN 
FREE-FLIGHT AERODYNAMIC RESEARCH 
MODELS. Carlos A. deMoraes, William K. 
Hagginbothom, Jr., and Ralph A. Falanga. 
December 1954. 25p. diagrs., photos. 
(NACA RM L54I15) 



INVESTIGATION AT TRANSONIC SPEEDS OF AERO- 
DYNAMIC CHARACTERISTICS OF A SEMICIRCULAR 
Am INLET IN THE ROOT OF A 450 SWEPTBACK 
WING. Charles D. Trescot, Jr., and Arvid L. 
Keith, Jr. March 1955. 30p. diagrs., photos., tab. 
(NACARM L55A05a) 



INVESTIGATION AT TRANSONIC SPEEDS OF AERO- 
DYNAMIC CHARACTERISTICS OF AN UNSWEPT 
SEMIELLIPTICAL AIR INLET IN THE ROOT OF A 
45° SWEPTBACK WING. Gene J. Bingham. 
September 1955. 37p. diagrs., photos., tabs. 
■(NACARM L55F22a) 



AN INVESTIGATION OF FLOW m CIRCULAR AND 
ANNULAR 90° BENDS WITH A TRANSITION IN 
CROSS SECTION. Stafford W. Wilbur. August 
1957. 32p. diagrs., photos., tabs. (NACA TN 3995) 



ANALYSIS OF SHOCK MOTION IN DUCTS DURING 
DISTURBANCES IN DOWNSTREAM PRESSURE. 
Herbert G. Hurrell. September 1957. lip. diagr. 
(NACA TN 4090) 



EXPERIMENTAL INVESTIGATION OF THE EF- 
FECTS OF SOME SHROUD DESIGN VARIABLES ON 
THE STATIC THRUST CHARACTERISTICS OF A 
SMALL-SCALE SHROUDED PROPELLER SUB- 
MERGED IN A WING. Robert T. Taylor. January 
1958. 23p. diagrs., photos. (NACA TN 4126) 



86 



(1) AERODYNAMICS 



TURBULENT FLOW THROUGH POROUS RESIST- 
ANCES SLIGHTLY INCLINED TO THE FLOW 
DIRECTION. Albert L. Loeffler, Jr., and Morris 
Perlmutter. February 1958. 30p. diagrs., photos. 
(NACA TN 4221) 



ON PAIRS OF SOLUTIONS OF A CLASS OF INTER- 
NAL VISCOUS FLOW PROBLEMS WITH BODY 
FORCES. Simon Ostrach and Lynn U. Albers. 
June 1958. 21p. diagrs., tabs. (NACA TN 4273) 



APPLICATION OF THE METHOD OF COORDINATE 
PERTURBATION TO UNSTEADY DUCT FLOW. 
Seymour C. Himmel, Case Institute of Technology. 
September 1958. (i), 152p. diagrs., tabs. 
(NACA TM 1439) 



INVESTIGATION OF BOILING BURNOUT AND FLOW 
STABILITY FOR WATER FLOWING IN TUBES. 
Warren H. Lowdermilk, Chester D. Lanzo, and 
Byron L. Siegel. September 1958. *lp. diagrs., 
tabs. (NACA TN 4382) 



(1.4.2. 1) 
DIFFUSERS 



EXPERIMENTAL INVESTIGATION OF TAIL-PIPE- 
BURNER DESIGN VARIABLES. W. A. Fleming, 
E. William Conrad, and A. W. Young. March 5, 
1951. 75p. diagrs., photos., tab. 
(NACA RM E50K22) 



AN INVESTIGATION AT MACH NUMBERS 2.98 AND 
2.18 OF AXIALLY SYMMETRIC FREE-JET DIFFU- 
SION WITH A RAM -JET ENGINE. Henry R. 
Hunczak. February 1952. 30p. photos., diagrs. 
(NACA RM E51L24) 



AN INVESTIGATION OF THE STREAM-TUBE 
POWER LOSSES AND AN IMPROVEMENT OF THE 
DIFFUSER-ENTRANCE NOSE IN THE LANGLEY 
8-FOOT TRANSONIC TUNNEL. Richard T. 
White omb, Melvin M. Carmel, and Francis G. 
Morgan, Jr. August 1952. 70p. diagrs., photos., 
tabs. (NACA RM L52E20) 



PERFORMANCE CHARACTERISTICS AT MACH 
NUMBERS TO 2.0 OF VARIOUS TYPES OF SIDE 
INLETS MOUNTED ON FUSELAGE OF PROPOSED 
SUPERSONIC AIRPLANE . rV - RECTANGULAR- 
COWL INLETS WITH TWO-DIMENSIONAL COM- 
PRESSION RAMPS- Paul C Simon. October 1952. 
35p. diagrs., photos. (NACA RM E52H29) 



TRANSONIC FLIGHT TESTS TO DETERMINE ZERO- 
LIFT DRAG AND PRESSURE RECOVERY OF NA- 
CELLES LOCATED AT THE WING ROOT ON A 45° 
SWEPTBACK WING AND BODY CONFIGURATION. 
Sherwood Hoffman and Austin L. Wolff. September 
1953. 31p. diagrs., photos., tabs. 
(NACA RM L53H20) 



INVESTIGATION OF TRANSLA TING-SPIKE SUPER- 
SONIC INLET AS MEANS OF MASS-FLOW CONTROL 
AT MACH NUMBERS OF 1.5, 1.8, AND 2,0. Gerald 
C. Gorton. October 1953. 23p. diagrs., photos., 
tabs. (NACA RM E53G10) 



PERFORMANCE OF A 16-INCH RAM-JET ENGINE 
WITH A CAN-TYPE COMBUSTOR AT MACH NUM- 
BERS OF 1.50 TO 2.16. Donald P. Hearth and 
Eugene Perchonok. August 1954. 30p. diagrs. 
(NACA RM E54G13) 



EXPERIMENTAL INVESTIGATION OF THE EF- 
FECTS OF SOME SHROUD DESIGN VARIABLES ON 
THE STATIC THRUST CHARACTERISTICS OF A 
SMALL-SCALE SHROUDED PROPELLER SUB- 
MERGED IN A WING. Robert T. Taylor. January 
1958. 23p. diagrs., photos. (NACA TN 4126) 



APPLICATION OF THE METHOD OF COORDINATE 
PERTURBATION TO UNSTEADY DUCT FLOW. 
Seymour C. Himmel, Case Institute of Technology. 
September 1958. (i), 152p. diagrs., tabs. 
(NACA TM 1439) 



(1.4.2. 1-1) 

Subsonic 



FORCE AND PRESSURE CHARACTERISTICS FOR A 
SERIES OF NOSE INLETS AT MACH NUMBERS 
FROM 1.59 TO 1.99. I - CONICAL SPIKE ALL- 
EXTERNAL COMPRESSION INLET WITH SUBSONIC 
COWL LIP. Fred T. Esenwein and Alfred S. 
Valerlno. January 19, 1951. 73p. diagrs., photos., 
tabs. (NACA RM E50J26) 



FORCE AND PRESSURE CHARACTERISTICS FOR A 
SERIES OF NOSE INLETS AT MACH NUMBERS 
FROM 1.59 TO 1.99. U - ISENTROPIC-SPKE ALL- 
EXTERNAL COMPRESSION INLET. L. J. Obery 
andG. W. Englert. February 9, 1951. 67p. 
diagrs., photos., tabs. (NACA RM E50J26a) 



FORCE AND PRESSURE CHARACTERISTICS FOR A 
SERIES OF NOSE INLETS AT MACH NUMBERS 
FROM 1.59 TO 1.99. Ill - CONICAL-SPIKE ALL- 
EXTERNAL -COMPRESSION INLET WITH SUPER- 
SONIC COWL LIP. Maynard I. Weinstein and Joseph 
Davids. February 14, 1951 51p. diagrs., tabs. 
(NACA RM E50J30) 



FORCE AND PRESSURE CHARACTERISTICS FOR A 
SERIES OF NOSE INLETS AT MACH NUMBERS 
FROM 1,59 TO 1.99. IV - CONICAL-SPIKE 
EXTERNAL-INTERNAL COMPRESSION INLET 
UTILIZING PERFORATED COWL . Robert T . 
Madden and Emll J. Kremzier. March 28, 1951. 
46p. diagrs., photos., tabs. (NACA RM E51B05) 



PERFORMANCE CHARACTERISTICS AT MACH 
NUMBERS TO 2.0 OF VARIOUS TYPES OF SIDE 
INLETS MOUNTED ON FUSELAGE OF PROPOSED 
SUPERSONIC AIRPLANE, n - INLETS UTILIZING 
HALF OF A CONICAL SPIKE. J. L. Allen and 
P. C. Simon. September 1952. 49p. diagrs., 
photos., tab. (NACA RM E52G08) 



PERFORMANCE CHARACTERISTICS AT MACH 
NUMBERS TO 2.00 OF VARIOUS TYPES OF SIDE 
INLETS MOUNTED ON FUSELAGE OF PROPOSED 
SUPERSONIC AIRPLANE. IH - NORMAL-WEDGE 
INLET WITH SEMICIRCULAR COWL. Fred T. 
Esenwein. October 1952. 43p. diagrs., photos. 
(NACA RM E52H20) 



87 



(1) AERODYNAMICS 



PERFORMANCE CHARACTERISTICS OF CANARD- 
TYPE MISSILE WITH WING -MOUNTED NACELLE 
ENGINES AT MACH NUMBERS 1.5 TO 2.0. EmllJ. 
Kremzier and Joseph Davids. November 1952. 
30p. diagrs., tab. (NACA RM E52J08) 



FORCE AND PRESSURE RECOVERY CHARACTER- 
ISTICS AT SUPERSONIC SPEEDS OF A CONICAL 
SPIKE INLET WITH BYPASSES DISCHARGING IN 
AN AXIAL DIRECTION. J. L. Allen and Andrew 
Beke, January 1953. 27p. diagrs., photos., tab. 
(NACA RM E52K14) 



EFFECT OF DIFFUSER DESIGN, DIFFUSER-EXIT 
VELOCITY PROFILE, AND FUEL DISTRIBUTION 
ON ALTITUDE PERFORMANCE OF SEVERAL 
AFTERBURNER CONFIGURATIONS. E. William 
Conrad, Frederick W. Schuize, and Karl H. Usow. 
July 1953. 63p. diagrs., photos., tab. 
(NACA RM E53A30) 



AN ANALYTICAL STUDY OF THE COMPARATIVE 
PERFORMANCE OF SDC AIR-INDUCTION SYSTEMS 
FOR TURBOJET-POWERED AIRPLANES DESIGNED 
TO OPERATE AT MACH NUMBERS UP TO 2.0. 
Earl C. Watson. October 1953. 46p. diagrs. 
(NACA RM A53H03) 



EXPERIMENTAL INVESTIGATION OF SCREECHING 
COMBUSTION IN FULL-SCALE AFTERBURNER. 
Karl H. Usow, Carl L. Meyer, and Frederick W. 
Schuize. December 1953. 62p. diagrs., photos., 
tab. (NACA RM E53I01) 



INVESTIGATION OF CONICAL SUBSONIC DIFFUS- 
ERS FOR RAM-JET ENGINES. John M. Farley and 
Henry J. Welna. March 1954. 40p. diagrs., 
photos., tabs. (NACA RM E53L15). 



PERFORMANCE CHARACTERISTICS OF SEVERAL 
SHORT ANNULAR DIFFUSERS FOR TURBOJET 
ENGINE AFTERBURNERS. William E. Mallett and 
James L. Harp, Jr. May 1954. 31p. diagrs., 
photo. (NACA RM E54B09) 



EFFECT OF MECHANICALLY INDUCED SINUSOIDAL 
AIR-FLOW OSCILLATIONS ON OPERATION OF A 
RAM-JET ENGINE. E. E. Dangle, A. J. Cervenka, 
and Eugene Perchonok. June 1954. 24p. diagrs., 
tab. (NACA RM E54D01) 



PRELIMINARY INVESTIGATION AT MACH 
NUMBER 1.9 OF SIMULATED WING-ROOT INLETS. 
Thomas G. Piercy and Maynard I. Weinstein. 
January 1955. 60p. diagrs., photos., tab. 
(NACA RM E54I24) 



A PRELIMINARY INVESTIGATION OF METHODS 
FOR IMPROVING THE PRESSURE -RECOVERY 
CHARACTERISTICS OF VARIABLE -GEOMETRY 
SUPERSONIC-SUBSONIC DIFFUSER SYSTEMS. 
Lowell E. Hasel and Archibald R. Sinclair. October 
1957. 57p. diagrs., photos. (NACA RM L57H02) 



AN APPROXIMATE METHOD FOR DESIGN OR 
ANALYSIS OF TWO-DIMENSIONAL SUBSONIC - 
FLOW PASSAGES. E. Floyd Valentine. April 
1958. 38p. diagrs., photo. (NACA TN 4241) 



SOME EFFECTS OF VANES AND OF TURBULENCE 
IN TWO-DIMENSIONAL WIDE-ANGLE SUBSONIC 
DIFFUSERS. Carl A. Moore, Jr., and Stephen J. 
Kline, Stanford University. June 1958. iii, 139p. 
diagrs., photos., tabs., film suppl. available on 
request. (NACA TN 4080) 



USE OF SHORT FLAT VANES FOR PRODUCING 
EFFICIENT WIDE-ANGLE TWO-DIMENSIONAL 
SUBSONIC DIFFUSERS. D. L. Cochran and S. J. 
Kline, Stanford University. September 1958. 135p. 
diagrs., photos., tabs. (NACA TN 4309) 



(1.4.2. 1.2) 
Supersonic 



FORCE AND PRESSURE CHARACTERISTICS FOR A 
SERIES OF NOSE INLETS AT MACH NUMBERS 
FROM 1.59 TO 1.99. I - CONICAL SPIKE ALL- 
EXTERNAL COMPRESSION INLET WITH SUBSONIC 
COWL LIP. Fred T. Esenwein and Alfred S. 
Valerlno. January 19, 1951. 73p. diagrs., photos., 
tabs. (NACA RM E50J26) 



FORCE AND PRESSURE CHARACTERISTICS FOR A 
SERIES OF NOSE INLETS AT MACH NUMBERS 
FROM 1.59 TO 1.99. U - ISENTROPIC -SPIKE ALL- 
EXTERNAL COMPRESSION INLET. L. J. Obery 
and G. W. Englert. February 9, 1951. 67p. 
diagrs., photos., tabs. (NACA RM E50J26a) 



FORCE AND PRESSURE CHARACTERISTICS FOR A 
SERIES OF NOSE INLETS AT MACH NUMBERS 
FROM 1.59 TO 1.99. HI - CONICAL-SPIKE ALL- 
EXTERNAL-COMPRESSION INLET WITH SUPER- 
SONIC COWL LIP. Maynard I. Weinstein and Joseph 
Davids. February 14, 1951. 51p. diagrs., tabs. 
(NACA RM E50J30) 



FORCE AND PRESSURE CHARACTERISTICS FOR A 
SERIES OF NOSE INLETS AT MACH NUMBERS 
FROM 1.59 TO 1.99. IV - CONICAL-SPIKE 
EXTERNAL -INTERNAL COMPRESSION INLET 
UTDLIZING PERFORATED COWL. Robert T. 
Madden and E mil J. Kremzier. March 28, 1951. 
46p. diagrs., photos., tabs. (NACA RM E51B05) 



DESIGN AND PERFORMANCE OF AN EXPERIMEN- 
TAL AXIAL-DISCHARGE MDCED-FLOW COM- 
PRESSOR, m - OVER-ALL PERFORMANCE OF 

IMPELLER ANDSUPERSONIC-DIFFUSER COMBI- 
NATION. Ward W. Wilcox and William H. Robbins. 
April 30, 1951. 26 p. diagrs., photo. 
(NACA RM E51A02) 



INVESTIGATION OF OFF-DESIGN PERFORMANCE 
OF SHOCK -IN -ROTOR TYPE SUPERSONIC 
BLADING. Robert C. Graham, John F. Klapprocn, 
and Frank J. Barina. May 7, 1951. 25 p. diagrs., 
photos. (NACA RM E51C22) 



INTERNAL FLOW AND BURNING CHARACTERIS- 
TICS OF 16-INCH RAM JET OPERATING IN A FREE 
JET AT MACH NUMBERS OF 1.35 AND 1.73. 
Eugene Perchonok and John M. Farley, May 21, 
1951. 37p. diagrs., photos., tab. 
(NACA RM E51C16) 



88 



(1) AERODYNAMICS 



INVESTIGATION AT MACH NUMBER 1.88 OF HALF 
OF A CONICAL-SPIKE DIFFUSER MOUNTED AS A 
SIDE INLET WITH BOUNDARY -LAYER CONTROL. 
H. Fred Goelzer and Edgar M. Cortright, Jr. 
September 1951. 38p. diagrs., photos. 
(NACA RM E51G06) 



ANALYTICAL AND EXPERIMENTAL INVESTIGA- 
TION OF INLET-ENGINE MATCHING FOR 
TURBOJET-POWERED AIRCRAFT AT MACH NUM- 
BERS UP TO 2.0. Carl F. Schueller and Fred T. 
Esenweirt. February 1952. 31p. diagrs., photos. 
(NACA RM E51K20) 



PERFORMANCE OF AN IMPULSE-TYPE SUPER- 
SONIC COMPRESSOR WITH STATORS. John F. 
Klapproth, GuyN. Ullman, and Edward R. Tysl. 
April 1952. 22p. diagrs., photo. 
(NACARM E52B22) 



EVALUATION OF FIVE CONICAL CENTER -BODY 
SUPERSONIC DIFFUSERS AT SEVERAL ANGLES OF 
ATTACK. Gerald W. Englert and Leonard J. Obery. 
May 1952. 29p. diagrs., photos., tab. 
(NACARME51L04) 



PERFORMANCE CHARACTERISTICS AT MACH 
NUMBERS TO 2.0 OF VARIOUS TYPES OF SIDE IN- 
LETS MOUNTED ON FUSELAGE OF PROPOSED 
SUPERSONIC AIRPLANE. I - TWO-DIMENSIONAL 
COMPRESSION-RAMP INLETS WITH SEMICIRCU- 
LAR COWLS. Alfred S. Valerino. July 1952. 43p. 
diagrs., photos., tab. (NACA RM E52E02) 



PRELIMINARY INVESTIGATION OF EFFECT OF 
ANGLE OF ATTACK ON PRESSURE RECOVERY 
AND STABILITY CHARACTERISTICS FOR A 
VERTICAL-WEDGE-NOSE INLET AT MACH NUM- 
BER OF 1.90. L. Abbott Leissler and Donald P. 
Hearth. August 1952. lip. diagrs., photos. 
(NACA RM E52E14) 



INVESTIGATION AT MACH NUMBER 2.93 OF HALF 
OF A CONICAL-SPIKE DIFFUSER MOUNTED AS A 
SIDE INLET WITH BOUNDARY-LAYER CONTROL. 
Thomas G. Piercy and Harry W. Johnson. 
September 1952. 39p. diagrs., photos. 
(NACA RM E52G23) 



PERFORMANCE CHARACTERISTICS AT MACH 
NUMBERS TO 2.0 OF VARIOUS TYPES OF SIDE 
INLETS MOUNTED ON FUSELAGE OF PROPOSED 
SUPERSONIC AIRPLANE. IV - RECTANGULAR- 
COWL INLETS WITH TWO-DIMENSIONAL COM- 
PRESSION RAMPS. Paul C. Simon- October 1952. 
35p. diagrs., photos. (NACA RM E52H29) 



SOME OBSERVATIONS OF FLOW AT THE THROAT 
OF A TWO-DIMENSIONAL DIFFUSER AT THE 
MACH NUMBER OF 3.85. James F. Connors and 
Richard R. Woollett. November 1952. 13p. photos, 
diagrs- (NACA RM E52I04) 



PERFORMANCE CHARACTERISTICS OF CANARD- 
TYPE MISSILE WITH WING-MOUNTED NACELLE 
ENGINES AT MACH NUMBERS 1.5 TO 2.0. Emil J. 
Kremzier and Joseph Davids. November 1952. 
30p. diagrs., tab. (NACA RM E52J08) 



PREUMINARY INVESTIGATION OF THE EFFECTS 
OF INLET ASYMMETRY ON THE PERFORMANCE 
OF CONVERGING-DIVERGING DIFFUSERS AT 
TRANSONIC SPEEDS. John S. Dennard and William 
J. Nelson. November 1952. 30p. diagrs., photos., 
tab. (NACA RM L52J20) 



INVESTIGATION AT SUPERSONIC SPEEDS OF AN 
INLET EMPLOYING CONICAL FLOW SEPARATION 
FROM A PROBE AHEAD OF A BLUNT BODY. 
Donald P. Hearth and Gerald C. Gorton. January 
1953. 32p. diagrs., photos., tab. 
(NACA RM E52K18) 



INVESTIGATION OF PRESSURE RECOVERY OF A 
SINGLE-CONICAL-SHOCK NOSE INLET AT MACH 
NLMBER 5.4. Harry Bernstein and Rudolph C. 
Haefeli. April 1953. 22p. diagrs., photos. 
(NACA RM E53A12^ 



INVESTIGATION OF A HALF-CONICAL SCOOP IN- 
LET MOUNTED AT FIVE ALTERNATE CIRCUM- 
FERENTIAL LOCATIONS AROUND A CIRCULAR 
FUSELAGE. PRESSURE -RECOVERY RESULTS AT 
A MACH NUMBER OF 2.01. Lowell E. Hasel, John 
L. Lankford, and A. W. Robins. June 1953. 41p. 
diagrs., photos., tab. (NACA RM L53D30b) 



INVESTIGATION OF 16-INCH IMPULSE-TYPE 
SUPERSONIC COMPRESSOR WITH ROTOR TURN- 
ING PAST AXIAL DIRECTION. John J. Jarklitch, 
Jr., and Melvin J. Hartmann. July 1953. 29p. 
diagrs., photos. (NACA RM E53D13) 



A PRELIMINARY INVESTIGATION AT MACH NUM- 
BER 1.91 OF AN INLET CONFIGURATION DESIGNED 
FOR INSENSITIVITY TO POSITIVE ANGLE-OF- 
ATTACK OPERATION. Milton A. Beheim. July 
1953. 18p. diagrs., photos. (NACA RM E53E20) 



THE EFFECT OF INITIAL RATE OF SUBSONIC 
DIFFUSION ON THE STABLE SUBCRITICAL MASS- 
FLOW RANGE OF A CONICAL SHOCK DIFFUSER. 
J. C. Nettles. July 1953. 23p. diagrs. 
(NACA RM E53E26) 



A COMPARISON OF SEVERAL SYSTEMS OF 
BOUNDARY-LAYER REMOVAL AHEAD OF A TYPI- 
CAL CONICAL EXTERNAL-COMPRESSION SIDE 
INLET AT MACH NUMBERS OF 1.88 AND 2.93. 
Thomas G. Piercy and Harry W. Johnson. 
September 1953. 58p. diagrs., photos. 
(NACA RM E53F16) 



UTILIZATION OF EXTERNAL -COMPRESSION DIF- 
FUSION PRINCIPLE IN DESIGN OF SHOCK-IN- 
ROTOR SUPERSONIC COMPRESSOR BLADING. 
John W. R. Creagh and John F. Klapproth. 
September 1953. 37p. diagrs., photos., tab. 
(NACARM E53F18) 



EFFECT OF CIRCUMFERENTIAL LOCATION ON 
ANGLE OF ATTACK PERFORMANCE OF TWIN 
HALF-CONICAL SCOOP-TYPE INLETS MOUNTED 
SYMMETRICALLY ON THE RM-10 BODY OF REV- 
OLUTION. Alfreds. Valerino, Donald B. 
Pennington, and Donald J. Vargo. September 1953. 
37p. diagrs., photos. (NACA RM E53G09) 



89 



(1) AERODYNAMICS 



AN ANALYTICAL STUDY OF THE COMPARATIVE 
PERFORMANCE OF SIX AIR-INDUCTION SYSTEMS 
FOR TURBOJET-POWERED AIRPLANES DESIGNED 
TO OPERATE AT MACH NUMBERS UP TO 2.0. 
Earl C. Watson. October 1953. 46p. diagrs. 
(NACA RM A53H03) 



PRELIMINARY INVESTIGATION OF THE TOTAL- 
PRESSURE -RECOVERY CHARACTERISTICS OF A 
SYMMETRIC AND AN ASYMMETRIC NOSE INLET 
OVER A WIDE RANGE OF ANGLE OF ATTACK AT 
SUPERSONIC MACH NUMBERS. Howards. Carter 
and Charles F. Merlet. December 1953. 27p. 
diagrs., photo. (NACA RM L53J30) 



INVESTIGATION OF A TRANSLATING-CONE INLET 
AT MACH NUMBERS FROM 1.5 TO 2.0. L. Abbott 
Leissler and William H. Sterbentz. May 1954. 29p. 
diagrs., photos., tab. (NACA RM E54B23) 



AN EXPERIMENTAL INVESTIGATION OF TWO- 
DIMENSIONAL, SUPERSONIC CASCADE-TYPE 
INLETS AT A MACH NUMBER OF 3.11. Edward 
Offenhartz. August 1954. 29p. diagrs., photos. 
(NACA RM L54E17) 



INVESTIGATION OF SUPERSONIC-COMPRESSOR 
ROTORS DESIGNED WITH EXTERNAL COMPRES- 
SION. Lawrence J. Jahnsen and Melvin J. 
Hartmann. September 1954. 41p. diagrs., photos. 
(NACA RM E54G27a) 



PERFORMANCE OF A SUPERSONIC RAMP INLET 
WITH INTERNAL BOUNDARY-LAYER SCOOP. 
Robert C. Campbell. November 1954. 14p. diagrs., 
photo. (NACA RM E54I01) 



PRELIMINARY INVESTIGATION AT MACH 
NUMBER 1.9 OF SIMULATED WING-ROOT INLETS. 
Thomas G. Piercy and Maynard I. Weinstein. 
January 1955. 60p. diagrs., photos., tab. 
(NACA RM E54I24) 



PRELIMINARY INVESTIGATION OF A TECHNIQUE 
OF PRODUCING A HEATED CORE IN A SUPER- 
SONIC WIND-TUNNEL STREAM. Morris D. 
Rousso and Milton A. Beheim. February 1955. 
22p. photos., diagrs. (NACA RM E54K02) 



A VARIABLE -GEOMETRY AXISYMMETRIC SUPER- 
SONIC INLET WITH TELESCOPING CENTERBODY. 
James F. Connors and Rudolph C. Meyer. 
September 1955. 27p. diagrs., photos., tabs. 
(NACA RM E55F30) 



PRELIMINARY ATTEMPTS AT ISOTHERMAL COM- 
PRESSION OF A SUPERSONIC AIR STREAM. 
E. Perchonok and F. Wilcox. January 1956. 33p. 
diagrs., photos., tab. (NACA RM E55I29a) 



AN ANALOG STUDY OF A SHOCK-POSITION DIF- 
FUSER CONTROL ON A SUPERSONIC TURBOJET 
ENGINE. David Novik. August 1956. 27p. diagrs. 
(NACA RM E56E09a) 



EFFECT OF FUSELAGE CIRCUMFERENTIAL 
INLET LOCATION ON DIFFUSER -DISCHARGE 
TOTAL-PRESSURE PROFILES AT SUPERSONIC 
SPEEDS. Emil J. Kremzier and Joseph F. 
Wasserbauer. October 1956. 14p. diagrs. 
(NACA RM E56G26) 



ANALYSIS OF SHOCK MOTION IN DUCTS DURING 
DISTURBANCES IN DOWNSTREAM PRESSURE. 
Herbert G. HurreU. September 1957. Up. diagr. 
(NACA TN 4090) 



A PRELIMINARY INVESTIGATION OF METHODS 

FOR IMPROVING THE PRESSURE -RECOVERY 
CHARACTERISTICS OF VARIABLE-GEOMETRY 
SUPERSONIC-SUBSONIC DIFFUSER SYSTEMS. 
Lowell E. Hasel and Archibald R. Sinclair. October 
1957. 57p. diagrs., photos, (NACA RM L57H02) 



(1.4.2.2) 
NOZZLES 



EXPERIMENTAL INVESTIGATION OF TAIL-PIPE- 
BURNER DESIGN VARIABLES. W. A. Fleming, 
E. William Conrad, and A. W. Young. March 5, 
1951. 75p. diagrs., photos., tab. 
(NACA RM E50K22) 



AIR-FLOW AND.POWER CHARACTERISTICS OF 
THE LANGLEY 16-FOOT TRANSONIC TUNNEL 
WITH SLOTTED TEST SECTION. Vernon G. Ward, 
Charles F. Whitcomb, and Merwin D. Pearson. 
July 1952. 50p. diagrs., photos. 
(NACA RM L52E01) 



SPREADING OF EXHAUST JET FROM 16-INCH RAM 
JET AT MACH NUMBER 2.0. Fred Wilcox and 
Donald Pennington. August 1952. 14p. diagrs. 
photo., tab. (NACA RM E52F25) 



AN INVESTIGATION OF THE STREAM-TUBE 
POWER LOSSES AND AN IMPROVEMENT OF THE 
DIFFUSER-EN TRANCE NOSE IN THE LANGLEY 
8-FOOT TRANSONIC TUNNEL. Richard T. 
Whitcomb, Melvin M. Carmel, and Francis G. 
Morgan, Jr. August 1952. 70p. diagrs., photos., 
tabs. (NACA RM L52E20) 



INTERNAL PERFORMANCE OF SEVERAL TYPES 
OF JET-EXIT CONFIGURATIONS FOR SUPERSONIC 
TURBOJET AIRCRAFT. William A. Fleming. 
January 1953. 28p. diagrs. (NACA RM E52K04) 



INTERNAL PERFORMANCE CHARACTERISTICS OF 
VARIABLE-THROAT PLUG- AND VANED-TYPE 
CONVERGENT -DIVERGENT NOZZLES. H. George 
Krull, FredW. Steffen, and Carl C. Ciepluch. 
June 1953. 34p. diagrs., photo. 
(NACA RM E53D09) 



PERFORMANCE CHARACTERISTICS OF A 
DOUBLE-CYLINDRICAL-SHROUD EJECTOR 
NOZZLE. Eli Reshotko. November 1953. 57p. 
diagrs., tab. (NACA RM E53H28) 



PRELIMINARY INVESTIGATION OF PERFORM- 
ANCE OF VARIABLE-THROAT EXTENDED-PLUG- 
TYPE NOZZLES OVER WIDE RANGE OF NOZZLE 
PRESSURE RATIOS. Carl C. Ciepluch, H. George 
Krull, and Fred W. Steffen. February 1954. 35p. 
diagrs., photos., tab. (NACA RM E53J28) 



PRELIMINARY INVESTIGATION OF PUMPING AND 
THRLST CHARACTERISTICS OF FULL-SIZE 
COOLING -AIR EJECTORS AT SEVERAL EXHAUST - 
GAS TEMPERATURES. W. K. Greathouse. April 
1954. 130p. diagrs., photos., tab. 
(NACA RM E54A18) 



90 



(1) AERODYNAMICS 



EFFECT OF JET-NOZZLE-EXPANSION RATIO ON 
DRAG OF PARABOLIC AFTERBODIES. Gerald W. 
Englert, Donald J. Vargo, and Robert W. Cubbison. 
April 1954. 26p. diagrs., photos. 
(NACARME54B12) 



EFFECT OF PLUG DESIGN ON PERFORMANCE 
CHARACTERISTICS OF CONVERGENT-PLUG 
EXHAUST NOZZLES. H. George Krull and William 
T. Beale. October 1954. 22p. diagrs., photos., tab. 
(NACA RM E54H05) 



EXPERIMENTAL DATA FOR FOUR FULL-SCALE 
CONICAL COOLING-AIR EJECTORS. C. C. 
Ciepluch and D. B. Fenn. November 1954. 41p. 
diagrs., photo., tab. (NACA RM E54F02) 



EFFECT OF DIVERGENCE ANGLE ON THE IN- 
TERNAL PERFORMANCE CHARACTERISTICS OF 
SEVERAL CONICAL CONVERGENT-DIVERGENT 
NOZZLES. Fred W. Steffen, H. George Krull, and 
Ralph F. Schmiedlin. November 1954. 24p. diagrs. 
(NACARM E54H25) 



INVESTIGATION AT SUPERSONIC SPEEDS OF THE 
EFFECT OF JET MACH NUMBER AND DIVER- 
GENCE ANGLE OF THE NOZZLE UPON THE PRES- 
SURE OF THE BASE ANNULUS OF A BODY OF 
REVOLUTION. August F. Bromm, Jr., and Robert 
M. O'Donnell. December 1954. 24p. diagrs., 
photos. (NACA RM L54I16) 



SOME STUDIES OF AXISYMMETRIC FREE JETS 
EXHAUSTING FROM SONIC AND SUPERSONIC 
NOZZLES INTO STILL AIR AND INTO SUPERSONIC 
STREAMS. Eugene S. Love and Carl E. Grigsby. 
May 1955. 11, 178p. diagrs., photos., tabs. 
(NACA RM L54L31) 



A METHOD FOR THE DESIGN OF POROUS-WALL 
WIND TUNNELS. George M. Stokes. January 
1956. 5 Op. diagrs., photo., tabs. 
(NACA RM L55J13a) 



INITIAL INCLINATION OF THE MIXING BOUNDARY 
SEPARATING AN EXHAUSTING SUPERSONIC JET 
FROM A SUPERSONIC AMBIENT STREAM. 
Eugenes. Love. January 1956. 30p. diagrs. 
(NACARM L55J14) 



JET EFFECTS ON BASE AND AFTERBODY PRES- 
SURES OF A CYLINDRICAL AFTERBODY AT TRAN- 
SONIC SPEEDS. James M. Cubbage, Jr. May 1956. 
50p. diagrs., photos. {NACARM L56C21) 



INTERNAL PERFORMANCE CHARACTERISTICS OF 
SHORT CONVERGENT -DIVERGENT EXHAUST NOZ- 
ZLES DESIGNED BY THE METHOD OF CHARACTER- 
ISTICS. H. George Krull and William T. Beale. 
July 1956. 17p. diagrs. (NACA RM E56D27a) 



EFFECTS OF EXTERNAL STREAM FLOW AND 
AFTERBODY VARIATIONS ON THE PERFORMANCE 
OF A PLUG NOZZLE AT HIGH SUBSONIC SPEEDS. 
R. J. Salmi and E. M. Cortright, Jr. October 1956. 
19p. diagrs. (NACA RM E56Flla) 



EFFECT OF SEVERAL DESIGN VARIABLES ON 
INTERNAL PERFORMANCE OF CONVERGENT- 
PLUG EXHAUST NOZZLES. H. George Krull, 
William T. Beale, and Ralph F. Schmiedlin. 
October 1956. 33p. diagrs., photos., tab. 
(NACA RM E56G20) 



BOUNDARIES OF SUPERSONIC AXISYMMETRIC 
FREE JETS. EugeneS. Love, Mildred J. Woodling, 
and Louise P. Lee. October 1956. 98p. diagrs. 
(NACA RM L56G18) 



NEAR NOISE FIELD OF A JET-ENGINE EXHAUST. 
Walton L. Howes, Edmund E. Callaghan, Willard D. 
Coles, and Harold R. Mull. Appendix B: CORRE- 
LATION COMPUTER. Channing C. Conger and 
Donald F. Berg. 1957. ii, 35p. diagrs., photos., 
tab. (NACA Rept. 1338. Supersedes TN 3763 and 
TN 3764) 



SHAPE OF INITIAL PORTION OF BOUNDARY OF 
SUPERSONIC AXISYMMETRIC FREE JETS AT 
LARGE JET PRESSURE RATIOS. Eugene S. Love 
and Louise P. Lee. January 1958. 29p. diagrs. 
(NACA TN 4195) 



LIMITED INVESTIGATION OF NOISE SUPPRESSION 
BY INJECTION OF WATER INTO EXHAUST OF 
AFTERBURNING JET ENGINE. Max C. Kurbjun. 
February 1958. 15p. diagrs., photo. 
(NACA RM L57L05) 



ACOUSTIC, THRUST, AND DRAG CHARACTERIS- 
TICS OF SEVERAL FULL-SCALE NOISE SUPPRES- 
SORS FOR TURBOJET ENGINES. Carl C. Ciepluch, 
Warren J. North, Willard D. Coles, and Robert J. 
Antl. April 1958. 48p. diagrs., photos. 
(NACA TN 4261) 



TRANSONIC DRAG OF SEVERAL JET-NOISE 
SUPPRESSORS. Warren J. North. April 1958. 34p. 
diagrs., photos. (NACA TN 4269) 



INTERNAL CHARACTERISTICS AND PERFORM- 
ANCE OF SEVERAL JET DEFLECTORS AT 
PRIMARY-NOZZLE PRESSURE RATIOS UP TO 
3.0. Jack G. McArdle. June 1958. ii, 107p. 
diagrs., photos., tabs. (NACA TN 4264) 



INTERNAL CHARACTERISTICS AND PERFORM- 
ANCE OF AN AERODYNAMICALLY CONTROLLED, 
VARIABLE-DISCHARGE CONVERGENT NOZZLE. 
Jack G. McArdle. July 1958. 33p. diagrs., photo., 
tabs. (NACA TN 4312) 



EXPERIMENTAL INVESTIGATION OF AXIAL AND 
NORMAL FORCE CHARACTERISTICS OF SKEWED 
NOZZLES. David J. Carter, Jr., and Allen R. 
Vick. September 1958. 40p. diagrs., photos. 
(NACA TN 4336) 



EFFECTS OF GROUND PROXIMITY ON THE 
THRUST OF A SIMPLE DOWNWARD-DIRECTED JET 
BENEATH A FLAT SURFACE. Kenneth P. 
Spreemann and Irving R. Sherman. September 1958. 
39p. diagrs., photos. (NACA TN 4407) 



(1.4.2.3) 

PIPES 



THE PRINCD7LES OF TURBULENT HEAT TRANS- 
FER. (Die Grundlagen des Turbulenten 
Warmeuberganges.) H. Reichardt. September 
1957. 45p. diagrs., tabs. (NACA TM 1408. 
Translation from Archiv fur die gesamte 
Warmetechnik, no. 6/7, 1951, p. 129-142) 



91 



(1) AERODYNAMICS 



VELOCITY AND FRICTION CHARACTERISTICS OF 
LAMINAR VISCOUS BOUNDARY-LAYER AND 
CHANNEL FLOW OVER SURFACES WITH EJEC- 
TION OR SUCTION. E. R, G, Eckert, Patrick L. 
Donoughe and Betty Jo Moore. December 1957. 
57p. diagrs., tabs. (NACA TN 4102) 



ON FULLY DEVELOPED CHANNEL FLOWS: SOME 
SOLUTIONS AND LIMITATIONS, AND EFFECTS OF 
COMPRESSIBILITY, VARIABLE PROPERTIES, 
AND BODY FORCES. Stephen H. Maslen. September 
1958. 46p. diagrs., tabs. (NACA TN 4319) 



INVESTIGATION OF BOILING BURNOUT AND FLOW 
STABILITY FOR WATER FLOWING IN TUBES. 
Warren H. Lowdermilk, Chester D. Lanzo, and 
Byron L. Siegel. September 1958. 51p. diagrs,, 
tabs. (NACA TN 4382) 



(1.4.2.4) 
BENDS 



AN INVESTIGATION OF FLOW IN CIRCULAR AND 
ANNULAR 90° BENDS WITH A TRANSITION IN 
CROSS SECTION. Stafford W. Wilbur. August 
1957. 32p. diagrs., photos., tabs. (NACA TN 3995) 



AN APPROXIMATE METHOD FOR DESIGN OR 
ANALYSIS OF TWO-DIMENSIONAL SUBSONIC - 
FLOW PASSAGES. E. Floyd Valentine. April 
1958. 38p. diagrs., photo. (NACA TN 4241) 



INTERNAL CHARACTERISTICS AND PERFORM- 
ANCE OF SEVERAL JET DEFLECTORS AT 
PRIMARY-NOZZLE PRESSURE RATIOS UP TO 
3.0. Jack G. McArdle. June 1958. 11, 107p. 
diagrs., photos., tabs. (NACA TN 4264) 



(1.4.3) 
EXITS 



INVESTIGATION AT MACH NUMBER 191 OF SIDE 
AND BASE PRESSURE DISTRIBUTIONS OVER CONI- 
CAL BOATTAILS WITHOUT AND WITH JET FLOW 
ISSUING FROM BASE. Edgar M. Cortright, Jr., and 
Albert H. Schroeder. September 1951. 59p. diagrs., 
photos. (NACA RM E51F26) 



INTERNAL PERFORMANCE OF SEVERAL TYPES 
OF JET-EXIT CONFIGURATIONS FOR SUPERSONIC 
TURBOJET AIRCRAFT. William A. Fleming. 
January 1953. 28p. diagrs. (NACA RM E52K04) 



INTERNAL PERFORMANCE CHARACTERISTICS OF 
VARIABLE -THROAT PLUG- AND VANED-TYPE 
CONVERGENT -DIVERGENT NOZZLES. H. George 
Krull, FredW. Steffen, and Carl C. Ciepluch. 
June 1953. 34p. diagrs., photo. 
(NACA RM E53D09) 



JET EFFECTS ON FLOW OVER AFTERBODIES IN 
SUPERSONIC STREAM. Edgar M. Cortright, Jr., 
and Fred D. Kochendorfer. November 1953. 31p. 
diagrs., photos. (NACA RM E53H25) 



PERFORMANCE CHARACTERISTICS OF A 
DOUBLE -CYLINDRICAL-SHROUD EJECTOR 
NOZZLE. EUReshotko. November 1953. 57p. 
diagrs., tab. (NACA RM E53H28) 



PRELIMINARY INVESTIGATION OF PERFORM- 
ANCE OF VARIABLE-THROAT EXTENDED-FLUG- 
TYPE NOZZLES OVER WIDE RANGE OF NOZZLE 
PRESSURE RATIOS. Carl C. Ciepluch, H, George 
Krull, and Fred W. Steffen. February 1954. 35p. 
diagrs., photos., tab. (NACA RM E53J28) 



EFFECT OF JET-NOZZLE-EXPANSION RATIO ON 
DRAG OF PARABOLIC AFTERBODIES. Gerald W. 
Englert, Donald J. Vargo, and Robert W. Cubbison. 
April 1954. 26p. diagrs., photos. 
(NACARME54B12) 



JET EFFECTS ON PRESSURE LOADING OF ALL- 
MOVABLE HORIZONTAL STABILIZER. Alfred S. 
Valerino. June 1954. 27p. diagrs., photo., tab. 
(NACA RM E54C24) 



PUMPING AND DRAG CHARACTERISTICS OF AN 
AIRCRAFT EJECTOR AT SUBSONIC AND SUPER- 
SONIC SPEEDS. Gerald C. Gorton. June 1954. 
19p. diagrs. (NACA RM E54D06) 



PRELIMINARY WIND-TUNNEL INVESTIGATION OF 
TWO TYPES OF JET- EXIT CONFIGURATIONS *OK 
CONTROL OF AIRCRAFT. Gerald W. Englert and 
L. Abbott Leissler. August 1954. 20p. diagrs. 
(NACA RM E54E27) 



EFFECT OF PLUG DESIGN ON PERFORMANCE 
CHARACTERISTICS OF CONVERGENT-PLUG 
EXHAUST NOZZLES. H. George KruU and William 
T. Beale. October 1954. 22p. diagrs., photos., tab. 
(NACA RM E54H05) 



EFFECT OF DIVERGENCE ANGLE ON THE IN- 
TERNAL PERFORMANCE CHARACTERISTICS OF 
SEVERAL CONICAL CONVERGENT-DIVERGENT 
NOZZLES, Fred W. Steffen, H. George Krull, and 
Ralph F. Schmiedltn. November 1954. 24p. diagrs. 
(NACA RM E54H25) 



EXPERIMENTAL INVESTIGATION OF DRAG OF 
AFTERBODIES WITH EXITING JET AT HIGH 
SUBSONIC MACH NUMBERS. Reino J. Salmi. 
November 1954. 28p. diagrs., photos. 
(NACA RM E54I13) 



DESIGN AND EVALUATION OF A TURBOJET 
EXHAUST SIMULATOR, UTILIZING A SOLID- 
PROPELLANT ROCKET MOTOR, FOR USE IN 
FREE-FLIGHT AERODYNAMIC RESEARCH 
MODELS. Carlos A. deMoraes, William K. 
Hagginbo thorn, Jr., and Ralph A. Falanga. 
December 1954. 25 p. diagrs., photos. 
(NACA RM L54I15) 



INVESTIGATION AT SUPERSONIC SPEEDS OF THE 
EFFECT OF JET MACH NUMBER AND DIVER- 
GENCE ANGLE OF THE NOZZLE UPON THE PRES- 
SURE OF THE BASE ANNULUS OF A BODY OF 
REVOLUTION. August F. Bromm, Jr., and Robert 
M. O'Donnell. December 1954. 24p. diagrs., 
photos. (NACA RM L54I16) 



92 



(1) AERODYNAMICS 



JET EFFECTS ON LONGITUDINAL TRIM OF AN 
AIRPLANE CONFIGURATION MEASURED AT MACH 
NUMBERS BETWEEN 1.2 AND 1.8. Robert F. Peck. 
January 1955. 17p. diagrs., photos. 
(NACARM L54J29a) 



SOME STUDIES OF AXISYMMETRIC FREE JETS 
EXHAUSTING FROM SONIC AND SUPERSONIC 
NOZZLES INTO STILL AIR AND INTO SUPERSONIC 
STREAMS. Eugene S. Love and Carl E. Grlgsby. 
May 1955. ii, 178p. diagrs., photos., tabs. 
(NACA RM L54L31) 



MATCHING OF AUXILIARY INLETS TO 
SECONDARY-AIR REQUIREMENTS OF AIRCRAFT 
EJECTOR EXHAUST NOZZLES. Donald P. Hearth, 
Gerald W. Englert, and Kenneth L. Kowalski. 
August 1955. 39p. diagrs. (NACA RM E55D21) 



A FREE-FLIGHT INVESTIGATION OF THE EFFECTS 
OF SIMULATED SONIC TURBOJET EXHAUST ON 
THE DRAG OF A BOATTAIL BODY WITH VARIOUS 
JET SIZES FROM MACH NUMBER 0.87 TO 1.50. 
Ralph A. Falanga. August 1955. 23p. diagrs., 
photos., tab. (NACA RM L55F09a) 



INITIAL INCLINATION OF THE MIXING BOUNDARY 
SEPARATING AN EXHAUSTING SUPERSONIC JET 
FROM A SUPERSONIC AMBIENT STREAM. 
EugeneS. Love. January 1956. 30p. diagrs. 
(NACA RM L55J14) 



RESULTS OF ROCKET MODEL TEST OF AN AIR- 
PLANE CONFIGURATION HAVING AN ARROW WING 
AND SLENDER FLAT -SIDED FUSELAGE. LIFT, 
DRAG, LONGITUDINAL STABILITY, LATERAL 
FORCE, AND JET EFFECTS AT MACH NUMBERS 
BETWEEN 1.0 AND 2.3. Robert F. Peck. 
February 1956. 26p. diagrs., photo. 
(NACA RM L55L29) 



A FREE-FLIGHT INVESTIGATION OF THE EF- 
FECTS OF A SONIC JET ON THE TOTAL-DRAG 
AND BASE-PRESSURE COEFFICIENTS OF A BOAT- 
TAIL BODY OF REVOLUTION FROM MACH NUM- 
BER 0.83 TO 1.70. Ralph A. Falanga. March 1956. 
18p. diagrs., photo., tab. (NACA RM L55L21) 



INTERACTION OF AN EXHAUST JET AND ELE- 
MENTARY CONTOURED SURFACES LOCATED IN A 
SUPERSONIC AIR STREAM. Joseph F. Wasserbauer 
and Gerald W. Englert. April 1956. 20p. diagrs., 
photo. (NACA RM E56A16) 



TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF A HEATED PROPULSTVE JET 
ON THE PRESSURE DISTRIBUTION ALONG A 
FUSELAGE OVERHANG. Elden S. Cornette and 
Donald H. Ward. April 1956. 42p. diagrs., photos., 
tab. (NACA RM L56A27) 



JET EFFECTS ON BASE AND AFTERBODY PRES- 
SURES OF A CYLINDRICAL AFTERBODY AT TRAN- 
SONIC SPEEDS. James M. Cubbage, Jr. May 1956. 
50p diagrs., photos. (NACARM L56C21) 



INTERNAL PERFORMANCE CHARACTERISTICS OF 
SHORT CONVERGENT -DIVERGENT EXHAUST NOZ- 
ZLES DESIGNED BY THE METHOD OF CHARACTER- 
ISTICS. H. George Krull and William T. Beale. 
July 1956. 17p. diagrs. (NACA RM E56D27a) 



EFFECT OF SEVERAL DESIGN VARIABLES ON 
INTERNAL PERFORMANCE OF CONVERGENT- 
PLUG EXHAUST NOZZLES. H. George Krull, 
William T. Beale, and Ralph F. Schmiedlin. 
October 1956. 33p. diagrs., photos., tab. 
(NACA RM E56G20) 



BOUNDARIES OF SUPERSONIC AXISYMMETRIC 
FREE JETS. EugeneS. Love, Mildred J . Woodling, 
and Louise P. Lee. October 1956. 98p. diagrs. 
(NACARM L56G18) 



FREE-FLIGHT INVESTIGATION AT TRANSONIC 
SPEEDS OF DRAG COEFFICIENTS OF A BOATTAII 
BODY OF REVOLUTION WITH A SIMULATED TUR- 
BOJET EXHAUST ISSUING AT THE BASE FROM 
CONICAL SHORT-LENGTH EJECTORS. Ralph A. 
Falanga and Abraham Leiss. December 1956. 34 p. 
ciiagrs., photos., tab. (NACA RM L56H23) 



SUMMARY OF SCALE -MODEL THRUST -REVERSER 
INVESTIGATION. John H. Povolny, Fred W. Steffen, 
and Jack G. McArdle. 1957. ii, 14p. diagrs., 
photos. (NACA Rept. 1314. Supersedes TN 3664) 



FAR NOISE FIELD OF AIR JETS AND JET ENGINES. 
Edmund E. Callaghan and Willard D. Coles. 1957. 
ii, 18p. diagrs., photos. (NACA Rept. 1329. 
Supersedes TN 3590; TN 3591) 



AN INVESTIGATION OF DISCHARGE AND THRUST 
CHARACTERISTICS OF FLAPPED OUTLETS FOR 
STREAM MACH NUMBERS FROM 0.40 TO 1.30. 
Allen R. Vick. July 1957. 47p. diagrs. 
(NACA TN 4007) 



SCREEN-TYPE NOISE REDUCTION DEVICES FOR 
GROUND RUNNING OF TURBOJET ENGINES. 
Willard D. Coles and Warren J. North. July 1957. 
23p. diagrs., photos. (NACA TN 4033) 



EXPERIMENTAL INVESTIGATION OF THE EF- 
FECTS OF SOME SHROUD DESIGN VARIABLES ON 
THE STATIC THRUST CHARACTERISTICS OF A 
SMALL-SCALE SHROUDED PROPELLER SUB- 
MERGED IN A WING. Robert T. Taylor. January 
1958. 23p. diagrs., photos. (NACA TN 4126) 



SHAPE OF INITIAL PORTION OF BOUNDARY OF 
SUPERSONIC AXISYMMETRIC FREE JETS AT 
LARGE JET PRESSURE RATIOS. Eugene S. Love 
and Louise P. Lee. January 1958. 29p. diagrs 
(NACA TN 4195) 



EFFECT OF JET TEMPERATURE ON JET -NOISE 
GENERATION. Vern G. Rollin. March 1958. 
13p. diagrs., photo. (NACA TN 4217) 



ACOUSTIC, THRUST, AND DRAG CHARACTERIS- 
TICS OF SEVERAL FULL-SCALE NOISE SUPPRES- 
SORS FOR TURBOJET ENGINES. Carl C Ciepluch, 
Warren J. North. Willard D. Coles, and Robert J. 
Antl. April 1958. 48p. diagrs ., photos. 
(NACA TN 4261) 



TRANSONIC DRAG OF SEVERAL JET -NOISE 
SUPPRESSORS. Warren J. North. April 1958. 
diagrs., photos. (NACA TN 4269) 



34p. 



(1) AERODYNAMICS 



93 



A PERFORMANCE ANALYSTS OF METHODS FOR 
HANDLING EXCESS INLET FLOW AT SUPERSONIC 
SPEEDS. Donald P. Hearth and James F. Connors. 
May 1958. 26p. diagrs., tab. (NACA TN 4270) 



INTERNAL CHARACTERISTICS AND PERFORM- 
ANCE OF SEVERAL JET DEFLECTORS AT 
PRIMARY-NOZZLE PRESSURE RATIOS UP TO 
3.0. Jack G. McArdle. June 1958. ii, 107p. 
diagrs., photos., tabs. (NACA TN 4264) 



USE OF THE COANDA EFFECT FOR OBTAINING 
JET DEFLECTION AND LIFT WITH A SINGLE 
FLAT-PLATE DEFLECTION SURFACE . Uwe H . 
von Giahn. June 1958. 49p. diagrs., tabs. 
(NACA TN 4272) 



INTERNAL CHARACTERISTICS AND PERFORM- 
ANCE OF AN AERODYNAMICALLY CONTROLLED, 
VARIABLE -DISCHARGE CONVERGENT NOZZLE. 

Jack G. McArdle. July 1958. 33p. diagrs., photo., 
tabs. (NACA TN 4312) 



EXPERIMENTAL INVESTIGATION OF AXIAL AND 
NORMAL FORCE CHARACTERISTICS OF SKEWED 
NOZZLES. David J. Carter, Jr., and Allen R. 
Vick. September 1958. 40p. diagrs., photos. 
(NACA TN 4336) 



USE OF THE COANDA EFFECT FOR JET DEFLEC- 
TION AND VERTICAL LIFT WITH MULTIPLE-FLAT- 
PLATE AND CURVED-PLATE DEFLECTION SUR- 
FACES. UweH. vonGlahn. APPENDIX B: 
ESTIMATED PERFORMANCE OF MULTIPLE- FLAT - 
PLATE DEFLECTORS- Thomas F. Gelder. 
September 1958. 54p. diagrs., photo., tabs. 
(NACA TN 4377) 



(1.4.4) 

JET PUMPS AND 

THMJST AUGMENTORS 



INVESTIGATION OF PERFORMANCE OF SEVERAL 
DOUBLE-SHROUD EJECTORS AND EFFECT OF 
VARIABLE-AREA EXHAUST NOZZLE ON SINGLE 
EJECTOR PERFORMANCE. C. W. Ellis, D. P. 
Hollister, and H. D. Wilsted. July 1952. 25p. 
diagrs., photos. (NACA RM E52D25) 



AN INVESTIGATION OF THE STREAM-TUBE 
POWER LOSSES AND AN IMPROVEMENT OF THE 
DIFFUSER-ENTRANCE NOSE IN THE LANGLEY 
8-FOOT TRANSONIC TUNNEL. Richard T. 
White omb, Melvin M. Carmel, and Francis G. 
Morgan, Jr. August 1952, 70p. diagrs., photos., 
tabs. (NACA RM L52E20) 



INTERNAL PERFORMANCE OF SEVERAL TYPES 
OF JET-EXIT CONFIGURATIONS FOR SUPERSONIC 
TURBOJET AIRCRAFT. William A. Fleming. 
January 1953. 28p. diagrs. (NACA RM E52K04) 



PERFORMANCE OF DOUBLE-SHROUD EJECTOR 
CONFIGURATION WITH PRIMARY PRESSURE 
RATIOS FROM 1.0 TO 10. Donald P. Hollister and 
William K. Greathouse. February 1953, 34p. 
diagrs., tabs. (NACA RM E52K17) 



ANALYSIS OF SEVERAL METHODS OF PUMPING 
COOLING AIR FOR TURBOJET-ENGINE AFTER- 
BURNERS. John C. Samuels and Herbert Yanowitz. 
February 1953, 54p. diagrs. (NACA RM E52K26) 



PERFORMANCE CHARACTERISTICS OF A 
DOUBLE -CYLINDRICAL-SHROUD EJECTOR 
NOZZLE. EliReshotko. November 1953. 57p. 
diagrs , tab. {NACA RM E53H28) 



PUMPING AND THRUST CHARACTERISTICS OF 
SEVERAL DIVERGENT COOLING-AIR EJECTORS 
AND COMPARISON OF PERFORMANCE WITH CON- 
ICAL AND CYLINDRICAL EJECTORS. S. C. 
Huntley and Herbert Yanowitz. January 1954. 42p. 
diagrs. (NACA RM E53J13) 



PRELIMINARY INVESTIGATION OF PUMPING AND 
THRUST CHARACTERISTICS OF FULL-SIZE 
COOLING-AIR EJECTORS AT SEVERAL EXHAUST- 
GAS TEMPERATURES. W. K. Greathouse. April 
1954. 130p. diagrs., photos., tab. 
(NACA RME54A18) 



PUMPING AND DRAG CHARACTERISTICS OF AN 
AIRCRAFT EJECTOR AT SUBSONIC AND SUPER- 
SONIC SPEEDS. Gerald C. Gorton. June 1954. 
19p. diagrs. (NACA RM E54D06) 



EXPERIMENTAL DATA FOR FOUR FULL-SCALE 
CONICAL COOLING-AIR EJECTORS. C. C. 

Ciepluch and D. B. Fenn. November 1954. 41p. 
diagrs., photo., tab. (NACA RM E54F02) 



MATCHING OF AUXILIARY INLETS TO 
SECONDARY-AIR REQUIREMENTS OF AIRCRAFT 
EJECTOR EXHAUST NOZZLES. Donald P. Hearth, 
Gerald W. Englert, and Kenneth L. Kowalskl. 
August 1955. 39p. diagrs. (NACA RM E55D21) 



FREE-FLIGHT INVESTIGATION AT TRANSONIC 
SPEEDS OF DRAG COEFFICIENTS OF A BOATTAIL 
BODY OF REVOLUTION WITH A SIMULATED TUR- 
BOJET EXHAUST ISSUING AT THE BASE FROM 
CONICAL SHORT-LENGTH EJECTORS. Ralph A. 
Falanga and Abraham Leiss. December 1956. 34p. 
diagrs., photos., tab. (NACA RM L56H23) 



EXPERIMENTAL INVESTIGATION OF AXIAL AND 
NORMAL FORCE CHARACTERISTICS OF SKEWED 
NOZZLES. David J. Carter, Jr., and Allen R. 
Vick. September 1958. 40p. diagrs,, photos. 
(NACA TN 4336) 



EFFECTS OF GROUND PROXIMITY ON THE 
THRUST OF A SIMPLE DOWNWARD- DIRECT ED JET 
BENEATH A FLAT SURFACE. Kenneth P. 
Spreemann and Irving R. Sherman. September 1958. 
39p. diagrs., photos. (NACA TN 4407) 



(1.4.5) 



DIFFUSION FACTOR FOR ESTIMATING LOSSES 
AND LIMITING BLADE LOADINGS IN AXIAL- 
FLOW -COMPRESS OR BLADE ELEMENTS. 
Seymour Lieblein, Francis C. Schwenk, and Robert 
L. B rode rick. June 1953. 43p. diagrs., tabs. 
(NACA RM E53D01) 



94 



(1) AERODYNAMICS 



INVESTIGATION OF AN AXIAL-FLOW COMPRES- 
SOR ROTOR HAVING NACA HIGH-SPEED BLADE 
SECTIONS (A 2 Iab SERIES) AT MEAN RADIUS 
RELATIVE INLET MACH NUMBERS UP TO 1.13. 
Melvyn Savage, JohnR. Erwin, and Robert P. 
Whitley. November 1953. 43p. diagrs., photos., 
tab: (NACA RM L53G02) 



GENERAL CONSIDERATIONS OF MACH NUMBER 
EFFECTS ON COMPRESSOR-BLADE DESIGN, 
John F. Klapproth. April 1954, 24p. diagrs., 
photos. {NACA RM E53L23a) 



AN EXPERIMENTAL INVESTIGATION OF TWO- 
DIMENSIONAL, SUPERSONIC CASCADE-TYPE 
INLETS AT A MACH NUMBER OF 3.11. Edward 
Offenhartz. August 1954. 29p. diagrs., photos. 
(NACA RM L54E17) 



ANALYSIS OF AERODYNAMIC BLADE -LOADING - 
LIMIT PARAMETERS FOR NACA 65^Cj A 10 )10 

COMPRESSOR -BLADE SECTIONS AT LOW SPEEDS, 
Melvyn Savage. April 1955. 32p. diagrs. 
(NACA RM L54L02a) 



THROAT-AREA DETERMINATION FOR A CASCADE 
OF DOUBLE-CIRCULAR-ARC BLADES. Linwood 
C. Wright and Richard Schwind. November 1955. 
20p. diagrs. (NACA RM E55H25a) 



SUMMARY OF SCALE-MODEL THRUST -REVERSER 
INVESTIGATION. John H. Povolny, Fred W. Steffen, 
and Jack G. McArdle. 1957. 11, 14p. diagrs., 
photos. (NACA Rept. 1314. Supersedes TN 3664) 



EFFECT OF SWEEP ON PERFORMANCE OF COM- 
PRESSOR BLADE SECTIONS AS INDICATED BY 
SWEPT-BLADE ROTOR, UNSWEPT-BLADE 
ROTOR, AND CASCADE TESTS. William R. 
Godwin. July 1957. 43p. diagrs. (NACA TN 4062) 



AERODYNAMIC FORCES ON A VIBRATING 
UNSTAGGERED CASCADE. (Luftkrafte an elnem 
schwingenden Gitter.) H. Sohngen. August 1957. 
16p. diagrs. (NACA TM 1412. Translation from 
Zeitschrift fur angewandte Mathematik und Mechanik, 
v. 35, no. 3, Mar. 1955, p. 81-88.) 



NACA 65 -SERIES COMPRESSOR ROTOR PERFORM- 
ANCE WITH VARYING ANNULUS-AREA RATIO, 
SOLIDITY, BLADE ANGLE, AND REYNOLDS NUM- 
BER AND COMPARISON WITH CASCADE RESULTS. 
Wallace M. SchuUe, John R. Erwin, and George C. 
Ashby, Jr. October 1957. 62p. diagrs., photos., 
tab. (NACA TN 4130. Supersedes RM L52L17) 



EXPERIMENTAL INVESTIGATION OF AN IMPULSE- 
TYPE SUPERSONIC COMPRESSOR ROTOR HAVING 
A TURNING OF 73° AT THE MEAN RADIUS. James 
R. Sterrett. June 1958. 35p. diagrs., photos., tabs. 
(NACA TN 4252) 



(1.4.5.1) 
THEORY 



UTILIZATION OF EXTERNAL-COMPRESSION DIF- 
FUSION PRINCIPLE IN DESIGN OF SHOCK -IN - 
ROTOR SUPERSONIC COMPRESSOR BLADING. 

John W. R. Creagh and John F. Klapproth. 
September 1953. 37p. diagrs., photos., tab. 
(NACA RM E53F18) 



REVIEW OF HIGH-PERFORMANCE AXIAL-FLOW- 
COMPRESSOR BLADE -ELEMENT THEORY. 
Seymour Liebleln. April 1954. 34p. diagrs. 
(NACARM E53L22) 



LOW -VELOCITY TURNING AS A MEANS OF MINI- 
MIZING BOUNDARY -LAYER ACCUMULATIONS 
RESULTING FROM SECONDARY FLOWS WITHIN 

TURBINE STATORS. Warner L. Stewart and Robert 
Y. Wong. May 1954. 18p. diagrs., photo. 
(NACARM E54B16) 



INVESTIGATION OF SUPERSONIC-COMPRESSOR 
ROTORS DESIGNED WITH EXTERNAL COMPRES- 
SION. Lawrence J. Jahnsen and Melvin J. 
Hartmann. September 1954. 41p. diagrs., photos. 
(NACA RM E54G27a) 



THROAT -AREA DETERMINATION FOR A CASCADE 
OF DOUBLE -CIRCULAR -ARC BLADES. Linwood 
C. Wright and Richard Schwind. November 1955. 
20p. diagrs. (NACA RM E55H25a) 



AERODYNAMIC DESIGN OF AXIAL-FLOW COM- 
PRESSORS. VOLUME I. Compressor and Turbine 
Research Division. Edited by Irving A. Johnsen and 
Robert O. Bullock. August 1956. xii, 406p. diagrs., 
photos., tab. (NACA RM E56B03) 



AERODYNAMIC DESIGN OF AXIAL-FLOW COM- 
PRESSORS. VOLUME II. Compressor and Turbine 
Research Division. Edited by Irving A. Johnsen and 
Robert O. Bullock. August 1956. x, 275p. diagrs., 
tabs. (NACA RM E56B03a) 



AERODYNAMIC DESIGN OF AXIAL -FLOW COM- 
PRESSORS. VOLUME HI. Compressor and Turbine 
Research Division. Edited by Irving A. Johnsen and 
Robert O. Bullock. August 1956. xii, 364p. diagrs., 
photos., tabs. (NACA RM E56B03b) 



AERODYNAMIC FORCES ON A VIBRATING 
UNSTAGGERED CASCADE. (Luftkrafte an elnem 
schwingenden Gitter.) H. Sohngen. August 1957. 
16p. diagrs. (NACA TM 1412. Translation from 
Zeitschrift fur angewandte Mathematik und Mechanik, 
v.35, no. 3, Mar. 1955, p. 81-88.) 



MAXIMUM THEORETICAL TANGENTIAL VELOCITY 
COMPONENT POSSIBLE FROM STRAIGHT-BACK 
CONVERGING AND CONVERGING-DIVERGING 
STATORS AT SUPERCRITICAL PRESSURE RATIOS. 
Thomas P. Moffitt. April 1958. 21p diagrs. 
(NACA TN 4271) 



STALL PROPAGATION IN A CASCADE OF AIR- 
FOILS. Anthony R. Kriebel, Barry S. Seidel, and 
Richard G. Schwind, Massachusetts Institute of 
Technology. June 1958. 122p. diagrs., photos., 
tabs. (NACA TN 4134) 



ANALYTICAL RELATION FOR WAKE MOMENTUM 
THICKNESS AND DIFFUSION RATIO FOR LOW- 
SPEED COMPRESSOR CASCADE BLADES. Seymour 
Liebleln. August 1958. 31p. diagrs. 
(NACA TN 4318) 



COMPRESSIBLE LAMINAR FLOW AND HEAT 
TRANSFER ABOUT A ROTATING ISOTHERMAL 
DISK. Simon Ostrach and Philip R. Thornton. 
August 1958. 18p. diagrs., tab. (NACA TN 4320) 



( 1 ) AERODYNAMICS 



95 



(1.4.5.2) 

EXPERIMENT 



INVESTIGATION OF OFF-DESIGN PERFORMANCE 
OF S40CK-IN -ROTOR TYPE SUPERSONIC 
BLADING. Robert C. Graham, John F. Klapproth, 
and Frank J. Barina. May 7, 1951. 25 p. diagrs., 
photos. (NACA RM E51C22) 



A TWO-DIMENSIONAL CASCADE STUDY OF THE 
AERODYNAMIC CHARACTERISTICS OF A 
TURBINE-ROTOR BLADE SUITABLE FOR AIR 
COOLING. Henry W. Plohr and Cavour H. Hauser. 
September 1951. 15p. diagrs., photos. 
(NACA RM E51G18) 



AN EXPERIMENTAL CASCADE STUDY OF THE 
EFFECTS OF A SOLIDITY REDUCTION ON THE 
TWO-DIMENSIONAL AERODYNAMIC CHARACTER- 
ISTICS OF A TURBINE-ROTOR BLADE SUITABLE 
FOR AIR COOLING. Henry W. Plohr and William J. 
Nusbaum. May 1952. 17p. diagrs., photos. 
(NACA RM E52B27) 



EXPERIMENTAL INVESTIGATION OF AN AXIAL- 
FLOW SUPERSONIC COMPRESSOR HAVING 
ROUNDED LEADING-EDGE BLADES WITH AN 
8-PERCENT MEAN THICKNESS-CHORD RATIO. 
Theodore J. Goldberg, Emanuel Boxer, and Peter T. 
Bernot. December 1953. 43p. diagrs., photos., 
tab. (NACA RM L53G16) 



LOW -SPEED CASCADE TESTS OF TWO 45° SWEPT 
COMPRESSOR BLADES WITH CONSTANT SPAN- 
WISE LOADING. Loren A. Beatty, Melvyn Savage, 
and James C. Emery. March 1954. 65p. diagrs., 
photos., tab. (NACA RM L53L07) 



REVIEW OF HIGH-PERFORMANCE AXIAL-FLOW- 
COMPRESSOR BLADE -ELEMENT THEORY. 
Seymour Liebleln. April 1954. 34p. diagrs. 
(NACARM E53L22) 



EXPERIMENTAL INVESTIGATION OF AN AXIAL- 
FLOW SUPERSONIC COMPRESSOR HAVING SHARP 
LEADING-EDGE BLADES WITH AN 8-PERCENT 
MEAN THICKNESS-CHORD RATIO AND OF THE 
EFFECT OF A LEADING-EDGE RADIUS. Theodore 
J. Goldberg. February 1955. 33p. diagrs., photo. 
(NACA RM L54K16) 



HIGH-SPEED CASCADE TESTS OF A BLADE SEC- 
TION DESIGNED FOR TYPICAL HUB CONDITIONS 
OF HIGH-FLOW TRANSONIC ROTORS Melvyn 
Savage, A. Richard Felix, and James C. Emery. 
September 1955. 48p. diagrs.. photos., tab. 
(NACA RM L55F07) 



THROAT-AREA DETERMINATION FOR A CASCADE 
OF DOUBLE -CIRCULAR -ARC BLADES. Linwood 
C. Wright and Richard Schwind. November 1955. 
20p. diagrs. (NACA RM E55H25a) 



USE OF SHADOWGRAPH TECHNIQUE IN THE 
ANALYSIS OF THE PERFORMANCE OF TWO 
SUPERSONIC AXIAL-FLOW COMPRESSOR ROTORS 
OPERATING OVER A MEAN RADIUS RELATIVE 
INLET MACH NUMBER RANGE OF 0.85 TO 1.7. 
Theodore J. Goldberg and James R. Sterrett. 
April 1956. 48p. diagrs., photos. 
(NACA RM L56A05) 



AERODYNAMIC DESIGN OF AXIAL-FLOW COM- 
PRESSORS. VOLUME I. Compressor and Turbine 
Research Division. Edited by Irving A. Johnsen and 
Robert O. Bullock. August 1956. xii, 406p. diagrs., 
photos., tab. (NACA RM E56B03) 



AERODYNAMIC DESIGN OF AXIAL -FLOW COM- 
PRESSORS. VOLUME II. Compressor and Turbine 
Research Division. Edited by Irving A. Johnsen and 
Robert O. Bullock. August 1956. x, 275p. diagrs., 
tabs. (NACA RM E56B03a) 



AERODYNAMIC DESIGN OF AXIAL-FLOW COM- 
PRESSORS. VOLUME III. Compressor and Turbine 
Research Division. Edited by Irving A. Johnsen and 
Robert O. Bullock. August 1956. xii, 364p. diagrs., 
photos., tabs. (NACA RM E56B03b) 



ANALYSIS OF EXPERIMENTAL LOW -SPEED LOSS 
AND STALL CHARACTERISTICS OF TWO- 
DIMENSIONAL COMPRESSOR BLADE CASCADES. 
Seymour Lieblein. March 1957. 64p. diagrs., 
tabs. (NACA RM E57A28) 



LOW-SPEED CASCADE INVESTIGATION OF THIN 
LOW-CAMBER NACA 65-SERIES BLADE SECTIONS 
AT HIGH INLET ANGLES. James C. Emery. June 
1957. 93p. diagrs.. tab. (NACA RM L57E03) 



LOW -SPEED CASCADE mVESTIGATION OF COM- 
PRESSOR BLADES HAVING LOADED LEADING 
EDGES. James C. Emery. January 1958. 76p. 
diagrs., photo., tabs. (NACA TN 4178. Supersedes 
RM L55J05) 



STALL PROPAGATION IN A CASCADE OF AIR- 
FOILS. Anthony R. Kriebel, Barry S. Seidel, and 
Richard G. Schwind, Massachusetts Institute of , 
Technology. June 1958. 122p. diagrs., photos., 
tabs. (NACA TN 4134) 



ANALYTICAL RELATION FOR WAKE MOMENTUM 
THICKNESS AND DIFFUSION RATIO FOR LOW- 
SPEED COMPRESSOR CASCADE BLADES. Seymour 
Lieblein. August 1958. 31p. diagrs. 
(NACA TN 4318) 



PERFORMANCE AT LOW SPEEDS OF COMPRESSOR 
ROTORS HAVING LOW-CAMBERED NACA 65- 
SERIES BLADES WITH HIGH INLET ANGLES AND 
LOW SOLIDITIES. James C. Emery and Paul W. 
Howard. August 1958. 28p. diagrs. 
(NACA TN 4344) 



044) 



INVESTIGATION OF AN AXIAL-FLOW COMPRES- 
SOR ROTOR HAVING NACA HIGH-SPEED BLADE 
SECTIONS (A 2 l8b SERIES) AT MEAN RADIUS 
RELATTVE INLET MACH NUMBERS UP TO 1.13. 
Melvyn Savage, JohnR. Erwin, and Robert P. 
Whitley. November 1953. 43p. diagrs., photos., 
tab. (NACA RM L53G02) 



96 



(1) AERODYNAMICS 



ANALYSIS OF AERODYNAMIC BLADE- LOADING - 
LIMIT PARAMETERS FOR NACA 65-(Cj o A 10 )10 

COMPRESSOR-BLADE SECTIONS AT LOW SPEEDS. 
Melvyn Savage. April 1955. 32p. diagrs. 
(NACA RM L54L02a) 



EFFECT OF SWEEP ON PERFORMANCE OF COM- 
PRESSOR BLADE SECTIONS AS INDICATED BY 
SWEPT-BLADE ROTOR, UNSWEPT-BLADE 
ROTOR, AND CASCADE TESTS. William R. 
Godwin. July 1957. 4 3p . diagrs. (NACA TN 4062) 



PRELIMINARY INVESTIGATION OF THE CHAR- 
ACTERISTICS OF A TWO-DIMENSIONAL WING AND 
PROPELLER WITH THE PROPELLER PLANE OF 
ROTATION IN THE WING-CHORD PLANE. David 
H. Hickey. August 1957. 12p. diagrs. 
(NACA RM A57F03) 



(1.4.7) 
BOUNDARY LAYER 



MATCHING OF AUXILIARY INLETS TO 
SECONDARY-AIR REQUIREMENTS OF AIRCRAFT 
EJECTOR EXHAUST NOZZLES. Donald P. Hearth, 
Gerald W. Englert, and Kenneth L. Kowalski. 
August 1955. 39p. dia-.rs. (NACA RM E55D21) 



A METHOD FOR THE DESIGN OF POROUS-WALL 
WIND TUNNELS. George M. Stokea. January 
1956. 50p. diagrs., photo., tabs. 
(NACA RM L55Jl3a) 



APPROXIMATE CALCULATION OF THE COMPRES- 
SIBLE TURBULENT BOUNDARY LAYER WITH 
HEAT TRANSFER AND ARBITRARY PRESSURE 
GRADIENT. EU Reshotko and Maurice Tucker. 
December 1957. 34p. diagrs. (NACA TN 4154) 



ON FLOW OF ELECTRICALLY CONDUCTING 
FLUIDS OVER A FLAT PLATE IN THE PRESENCE 
OF A TRANSVERSE MAGNETIC FIELD. Vernon J . 
Rossow. 1958. ii, 20p. diagrs., tabs. 
(NACA Rept. 1358. Supersedes TN 3971) 



THE INTERACTION OF A REFLECTED SHOCK 
WAVE WITH THE BOUNDARY LAYER IN A SHOCK 
TUBE. Herman Mark, Cornell University. March 
1958. ii, 128p. diagrs., photos., tabs. 
(NACA TM 1418) 



AN EXPERIMENTAL STUDY OF THE TURBULENT 
BOUNDARY LAYER ON A SHOCK -TUBE WALL. 
Paul B. Gooderum June 1958. 63p. diagrs., 
photos., tab. (NACA TN 4243) 



ON PAIRS OF SOLUTIONS OF A CLASS OF INTER- 
NAL VISCOUS FLOW PROBLEMS WITH BODY 
FORCES. Simon Ostrach and Lynn U. Albers. 
June 1958. 21 p. diagrs., tabs. (NACA TN 4273) 



PRANDTL NUMBER EFFECTS ON UNSTEADY 
FORCED-CONVECTION HEAT TRANSFER. E. M. 
Sparrow and J. L. Gregg. June 1958. 14p. diagrs., 
tab. (NACA TN 4311) 



ON POSSIBLE SIMILARITY SOLUTIONS FOR 
THREE-DIMENSIONAL INCOMPRESSIBLE LAMINAR 
BOUNDARY-LAYER FLOW OVER DEVELOPABLE 
SURFACES AND WITH PROPORTIONAL MAIN- 
STREAM VELOCITY COMPONENTS. Arthur G. 
Hansen, Case Institute of Technology. September 
1958. (ii), 79p. diagrs. (NACA TM 1437) 



NATURAL CONVECTION INSIDE A FLAT ROTATING 
CONTAINER. Simon Ostrach and Willis H. Braun. 
September 1958. 27p. diagrs. (NACA TN 4323) 



A NONLINEAR THEORY FOR PREDICTING THE 
EFFECTS OF UNSTEADY LAMINAR, TURBULENT, 
OR TRANSITIONAL BOUNDARY LAYERS ON THE 
ATTENUATION OF SHOCK WAVES IN A SHOCK 
TUBE WITH EXPERIMENTAL COMPARISON. / 
Robert L. Trimpi and Nathaniel B. Cohen. September 
1958. 105p. diagrs., photos., tab. (NACA TN 4347) 



SOME NUMERICAL SOLUTIONS OF SIMILARITY 
EQUATIONS FOR THREE-DIMENSIONAL LAMINAR 
INCOMPRESSIBLE BOUNDARY-LAYER FLOWS. 
Peggy L. Yohner and Arthur G. Hansen. September 
1958. 76p. diagrs., tabs. (NACA TN 4370) 



(1.4.7. 1) 
CHARACTERISTICS 



AN INVESTIGATION OF THE STREAM- TUBE 
POWER LOSSES AND AN IMPROVEMENT OF THE 
DIFFUSER-ENTRANCE NOSE IN THE LANGLEY 
8-FOOT TRANSONIC TUNNEL. Richard T. 
Whitcomb, Melvin M. Carmel, and Francis G. 
Morgan, Jr. August 1952. 70p. diagrs., photos., 
tabs. (NACA RM L52E20) 



EFFECT OF CIRCUMFERENTIAL LOCATION ON 
ANGLE OF ATTACK PERFORMANCE OF TWIN 
HALF-CONICAL SCOOP -TYPE INLETS MOUNTED 
SYMMETRICALLY ON THE RM-10 BODY OF REV- 
OLUTION. Alfred S. Valerino, Donald B. 
Pennington, and Donald J. Vargo. September 1953. 
37p. diagrs., photos. (NACA RM E53G09) 



LOW-VELOCITY TURNING AS A MEANS OF MINI- 
MIZING BOUNDARY -LAYER ACCUMULATIONS 
RESULTING FROM SECONDARY FLOWS WITHIN 
TURBINE STATORS. Warner L. Stewart and Robert 
Y. Wong. May 1954. 18p. diagrs., photo. 
(NACA RM E54B16) 



CORRELATION OF TURBINE-BLADE -ELEMENT 
LOSSES BASED ON WAKE MOMENTUM THICKNESS 
WITH DIFFUSION PARAMETER FOR A SERIES OF 
SUBSONIC TURBINE BLADES IN TWO- 
DIMENSIONAL CASCADE AND FOR FOUR TRAN- 
SONIC TURBINE ROTORS. Robert Y. Wong and 
Warner L. Stewart. April 1955. 31p. diagrs. 
(NACARM E55B08) 



A VARIABLE-GEOMETRY AXTSYMMETRIC SUPER- 
SONIC INLET WITH TELESCOPING CENTERBODY . 
James F. Connors and Rudolph C. Meyer. 
September 1955. 27p. diagrs., photos., tabs. 
(NACA RM E55F30) 



VISUALIZATION OF ROTOR TIP SECONDARY 
FLOWS WITH BLADE TIP AIR DISCHARGE AND 

SUCTION IN A LOW-SPEED TURBINE. Millon G. 
Kofskey and Hubert W. Allen. August 1956. 28p. 
diagrs.. photos. (NACA RM E56E16) 



97 



(1) AERODYNAMICS 



A PRELIMINARY INVESTIGATION OF METHODS 
FOR IMPROVING THE PRESSURE -RECOVERY 
CHARACTERISTICS OF VARIABLE-GEOMETRY 
SUPERSONIC-SUBSONIC DIFFUSER SYSTEMS. 
Lowell E. Hasel and Archibald R. Sinclair. October 
1957. 57p. diagrs., photos. {NACA RM L57H02) 



MOMENTUM TRANSFER FOR FLOW OVER A 
FLAT PLATE WITH BLOWING. H. S. Mickley 
and R. S. Davis, Massachusetts Institute of 
Technology. November 1957. 64p. diagrs. , tabs. 
(NACA TN 4017) 



EFFECT OF WALL COOLING ON INLET PARAME- 
TERS OF A SCOOP OPERATING IN A TURBULENT 
BOUNDARY LAYER ON A FLAT OR CONICAL SUR- 
FACE FOR MACH NUMBERS 2 TO 10. Andrew Beke. 
March 1958. 21p. diagrs., tabs. 
(NACA TN 4153) 



APPROXIMATE SOLUTIONS OF A CLASS OF SIMI- 
LARITY EQUATIONS FOR THREE-DIMENSIONAL, 
LAMINAR, INCOMPRESSIBLE BOUNDARY-LAYER 
FLOWS. Arthur G. Hansen and Howard Z. Herzig. 
September 1958. 26p. diagrs. (NACA TN 4375) 



(1.4.7.2) 
CONTROL 



INVESTIGATION AT MACH NUMBER 1.88 OF HALF 
OF A CONICAL-SPIKE DIFFUSER MOUNTED AS A 
SIDE INLET WITH BOUNDARY- LAYER CONTROL. 
H. Fred Goelzer and Edgar M. Cortright, Jr. 
September 1951. 38p. diagrs., photos. 
(NACA RM E51G06) 



EVALUATION OF FIVE CONICAL CENTER -BODY 
SUPERSONIC DIFFUSERS AT SEVERAL ANGLES OF 
ATTACK. Gerald W. Englert and Leonard J. Obery. 
May 1952. 29p. diagrs., photos., tab. 
(NACARM E51L04) 



EXPERIMENTAL INVESTIGATION OF AXIAL-FLOW 
COMPRESSOR STATOR BLADES DESIGNED TO 
OBTAIN HIGH TURNING ANGLES BY MEANS OF 
BOUNDARY-LAYER SUCTION. G. R. Costello, 
R. L. Cummings, and G. K. Serovy. June 1952. 
22p. diagrs., photos., tab. (NACA RM E52D18) 



INVESTIGATION AT MACH NUMBER 2.93 OF HALF 
OF A CONICAL-SPIKE DIFFUSER MOUNTED AS A 
SIDE INLET WITH BOUNDARY-LAYER CONTROL. 
Thomas G. Piercy and Harry W. Johnson. 
September 1952. 39p. diagrs., photos. 
(NACA RM E52G23) 



INVESTIGATION OF A HALF-CONICAL SCOOP IN- 
LET MOUNTED AT FIVE ALTERNATE CIRCUM- 
FERENTIAL LOCATIONS AROUND A CIRCULAR 
FUSELAGE. PRESSURE-RECOVERY RESULTS AT 
A MACH NUMBER OF 2.01. Lowell E. Hasel, John 
L. Lankford, and A. W. Robins. June 1953. 41 p. 
diagrs., photos., tab. (NACA RM L53D30b) 



A COMPARISON OF SEVERAL SYSTEMS OF 
BOUNDARY -LAYER REMOVAL AHEAD OF A TYPI- 
CAL CONICAL EXTERNAL -COMPRESSION SIDE 
INLET AT MACH NUMBERS OF 1.88 AND 2.93. 
Thomas G. Piercy and Harry W. Johnson. 
September 1953. 58p. diagrs., photos. 
(NACA RM E53F16) 



INVESTIGATION AT TRANSONIC SPEEDS OF AERO- 
DYNAMIC CHARACTERISTICS OF A SEMIELLIPTI- 
CAL AJH INLET IN THE ROOT OF A 45° SWEPT - 
BACK WING. Robert R. Howell and Charles D- 
Trescot. Jr. December 1953. 39p. diagrs., 
photos., tabs. (NACA RM L53J22a) 



PERFORMANCE OF A SUPERSONIC RAMP INLET 
WITH INTERNAL BOUNDARY-LAYER SCOOP. 
Robert C. Campbell. November 1954. 14p. diagrs., 
photo. (NACA RM E54I01) 



EFFECT OF WALL COOLING ON INLET PARAME- 
TERS OF A SCOOP OPERATING IN A TURBULENT 
BOUNDARY LAYER ON A FLAT OR CONICAL SUR- 
FACE FOR MACH NUMBERS 2 TO 10. Andrew Beke. 
March 1958. 21p. diagrs., tabs. 
(NACA TN 4153) 



98 



(1) AERODYNAMICS 



(1.5) 
Propellers 



EXPERIMENTAL INVESTIGATION OF THE EF- 
FECTS OF SOME SHROUD DESIGN VARIABLES ON 
THE STATIC THRUST CHARACTERISTICS OF A 
SMALL-SCALE SHROUDED PROPELLER SUB- 
MERGED IN A WING. Robert T. Taylor. January 
1958. 23p. diagrs., photos. (NACA TN 4126) 



(1.5.1) 
THEORY 



A WIND-TUNNEL INVESTIGATION OF THE AERO- 
DYNAMIC CHARACTERISTICS OF A FULL-SCALE 
SUPERSONIC-TYPE THREE-BLADE PROPELLER 
AT MACH NUMBERS OF 0.96. Albert J. Evans and 
George Liner. July 1953. 61p. diagrs., photo. 
(NACA RM L53FOI) 



MEASUREMENT AND CALCULATION OF BLADE 
TORSIONAL DEFLECTION OF THREE SUPERSONIC- 
TYPE PROPELLERS. Arthur E. Allis and Willard E. 
Foss, Jr. May 1954. 35p. diagrs., photos. 
(NACA RM L53I16) 



INVESTIGATION OF THE NORMAL FORCE 
ACCOMPANYING THRUST -AXIS INCLINATION OF 
THE NACA 1.167-(0)(03)-058 AND THE NACA 
l.l67-(0)(05)-058 THREE-BLADE PROPELLERS AT 
FORWARD MACH NUMBERS TO 0.90. Fred A. 
Demele and William R. Otey. June 1954. 31p. 
diagrs., photo., tab. (NACA RM A54D22) 



EFFECT OF BLADE-SECTION CAMBER ON AERO- 
DYNAMIC CHARACTERISTICS OF FULL-SCALE 
SUPERSONIC-TYPE PROPELLERS AT MACH NUM- 
BERS TO 1.04. Julian D. Maynard, John M. Swlhart, 
and Harry T. Norton, Jr. October 1956. 79p. 
diagrs.. photos., tab. (NACA RM L56E10) 



(1.5.2) 
DESIGN VARIABLES 



MEASUREMENT AND CALCULATION OF BLADE 
TORSIONAL DEFLECTION OF THREE SUPERSONIC- 
TYPE PROPELLERS. Arthur E. Allis and Willard E. 
Foss, Jr. May 1954. 35p. diagrs., photos. 
(NACA RM L53I16) 



AERODYNAMIC CHARACTERISTICS AT HIGH 
SPEEDS OF RELATED FULL-SCALE PROPELLERS 
HAVING DIFFERENT BLADE-SECTION CAMBERS. 
Julian D. Maynard and LelandB. Salters, Jr. 1957. 
11, 24p. diagrs., photos., tab. (NACA Rep t. 1309. 
Supersedes RM L8E06) 



(1. 5.2. 1) 
BLADE SECTIONS 



WAKE SURVEYS IN THE SLIPSTREAM OF A FULL- 
SCALE SUPERSONIC-TYPE THREE-BLADE 
PROPELLER AT MACH NUMBERS TO 0.96. John 
M Swihart and Harry T. Norton, Jr. October 1953. 
33p. diagrs., photo. (NACA RM L53I09) 



MEASUREMENT AND CALCULATION OF BLADE 
TORSIONAL DEFLECTION OF THREE SUPERSONIC- 
TYPE PROPELLERS. Arthur E. Allis and Willard E. 
Foss, Jr. May 1954. 35p. diagrs., photos. 
(NACA RM L53I16) 



INVESTIGATION OF THE NORMAL FORCE 
ACCOMPANYING THRUST-AXIS INCLINATION OF 
THE NACA 1.167-(0)(03)-058 AND THE NACA 
1.167-(0)(05)-058 THREE-BLADE PROPELLERS AT 
FORWARD MACH NUMBERS TO 0.90. Fred A. 
Demele and William R. Otey. June 1954. 31p. 
diagrs., photo., tab. (NACA RM A54D22) 



THE EFFECT OF TRAILING-EDGE BLUNTNESS 
ON THE PERFORMANCE OF A SMALL-SCALE 
SUPERSONIC PROPELLER AT FORWARD MACH 
NUMBERS TO 0.92. Fred A. Demele and Carl D. 
Kolbe. January 1956. 66p. diagrs., photo., tabs. 
(NACARM A55J12) 



FLIGHT MEASUREMENTS OF SECTION EFFI- 
CIENCY, THRUST, AND POWER OF A SUPERSONIC - 
TYPE PROPELLER AT MACH NUMBERS TO 0.9. 
Jerome B. Ham mack and Thomas C. O'Bryan. 
January 1956. 38p. diagrs., photos., tab. 
(NACA RM L55121) 



FLIGHT MEASUREMENTS OF THE VIBRATORY 
BENDING AND TORSION STRESS ON A 
SUPERSONIC-TYPE PROPELLER FOR FLIGHT 
MACH NUMBERS UP TO 0.95. Thomas C. O'Bryan. 
July 1956. 22p. diagrs., photos., tab. 
(NACA RM L56D20a) 



EFFECT OF BLADE-SECTION CAMBER ON AERO- 
DYNAMIC CHARACTERISTICS OF FULL-SCALE 
SUPERSONIC -TYPE PROPELLERS AT MACH NUM- 
BERS TO 1.04. Julian D. Maynard, JohnM. Swihart, 
and Harry T. Norton, Jr. October 1956. 79p. 
diagrs., photos., tab. (NACARM L56E10) 



AERODYNAMIC CHARACTERISTICS AT HIGH 
SPEEDS OF RELATED FULL-SCALE PROPELLERS 
HAVING DIFFERENT BLADE -SECTION CAMBERS. 
Julian D. Maynard and Leland B . Salters, Jr. 1957. 
li, 24p. diagrs., photos., tab. (NACA Rept. 1309. 
Supersedes RM L8E06) 



FLIGHT INVESTIGATION OF A SUPERSONIC PRO- 
PELLER ON A PROPELLER RESEARCH VEHICLE 
AT MACH NUMBERS TO 1.01. Jerome B. 
Ham mack, Max C. Kurbjun, and Thomas C. 
O'Bryan. July 1957. 43p. diagrs., photos. 
(NACA RM L57E20) 



EFFECT OF ADVANCE RATIO ON FLIGHT PER- 
FORMANCE OF A MODIFIED SUPERSONIC PRO- 
PELLER. Jerome B. Hammack and Thomas C. 
O'Bryan. September 1958. 20p. diagrs., photos. 
(NACA TN 4389) 



(1) AERODYNAMICS 



99 



(1.5.-2.2) 
SOLIDITY 



AN INVESTIGATION OF SINGLE- AND DUAL- 
ROTATION PROPELLERS AT POSITIVE AND 
NEGATIVE THRUST, AND IN COMBINATION WITH 
AN NACA 1 -SERIES D-TYPE COWLING AT MACH 
NUMBERS UP TO 0.84. Robert M. Reynolds, 
Robert I. Sammonds, and John H. Walker. 1957. 
ii, 58p. diagrs., photos., tabs. (NACA Rept. 1336) 



(1.5.2.4) 
BLADE PLAN FORMS 



FLIGHT INVESTIGATION OF A SUPERSONIC PRO- 
PELLER ON A PROPELLER RESEARCH VEHICLE 
AT MACH NUMBERS TO 1.01. Jerome B. 
Hammack, Max C. Kurbjun, and Thomas C. 
O'Bryan. July 1957. 43p. diagrs., photos. 
(NACA RM L57E20) 



EFFECT OF ADVANCE RATIO ON FLIGHT PER- 
FORMANCE OF A MODIFIED SUPERSONIC PRO- 
PELLER. Jerome B. Hammack and Thomas C. 
O'Bryan. September 1958. 20p. diagrs., photos. 
(NACA TN 4389) 



(1.5.2.5) 
MACH NUMBER EFFECTS 



A WIND-TUNNEL INVESTIGATION OF THE AERO- 
DYNAMIC CHARACTERISTICS OF A FULL-SCALE 
SUPERSONIC-TYPE THREE-BLADE PROPELLER 
AT MACH NUMBERS OF 0.96. Albert J. Evans and 
George Liner. July 1953. 61p. diagrs., photo. 
(NACA RM L53F01) 



WAKE SURVEYS IN THE SLIPSTREAM OF A FULL- 
SCALE SUPERSONIC-TYPE THREE-BLADE 
PROPELLER AT MACH NUMBERS TO 0.96. John 
M. Swihart and Harry T. Norton, Jr. October 1953. 
33p. diagrs., photo. (NACA RM L53I09) 



MEASUREMENT AND CALCULATION OF BLADE 
TORSIONAL DEFLECTION OF THREE SUPERSONIC- 
TYPE PROPELLERS. Arthur E. Allis and Willard E. 
Foss, Jr. May 1954. 35p. diagrs., photos. 
(NACA RM L53I16) 



INVESTIGATION OF THE NORMAL FORCE 
ACCOMPANYING THRUST -AXIS INCLINATION OF 
THE NACA 1.167-(0)(03)-058 AND THE NACA 
1.167-(0)(05)-058 THREE-BLADE PROPELLERS AT 
FORWARD MACH NUMBERS TO 0.90. Fred A. 
Demele and WiUiam R. Otey. June 1954. 31p. 
diagrs., photo., tab. (NACA RM A54D22) 



THE EFFECT OF TRAILING-EDGE BLUNTNESS 
ON THE PERFORMANCE OF A SMALL-SCALE 
SUPERSONIC PROPELLER AT FORWARD MACH 
NUMBERS TO 0.92. Fred A. Demele and Carl D. 
Kolbe. January 1956. 66p. diagrs., photo., tabs. 
(NACARM A55J12) 



FLIGHT MEASUREMENTS OF SECTION EFFI- 
CIENCY, THRUST, AND POWER OF A SUPERSONIC- 
TYPE PROPELLER AT MACH NUMBERS TO 0.9. 
Jerome B. Hammack and Thomas C. O'Bryan. 
January 1956. 38p. diagrs., photos., tab. 
(NACA RM L55I21) 



FLIGHT MEASUREMENTS OF THE VIBRATORY 
BENDING AND TORSION STRESS ON A 
SUPERSONIC-TYPE PROPELLER FOR FLIGHT 
MACH NUMBERS UP TO 95 Thomas C. O'Bryan. 
July 1956. 22p. diagrs., photos., tab. 
(NACA RM L56D20a) 



EFFECT OF BLADE-SECTION CAMBER ON AERO- 
DYNAMIC CHARACTERISTICS OF FULL-SCALE 
SUPERSONIC-TYPE PROPELLERS AT MACH NUM- 
BERS TO 1.04. Julian D. Maynard, John M. Swihart, 
and Harry T. Norton, Jr. October 1956. 79p. 
diagrs., photos., tab. (NACA RM L56E10) 



AERODYNAMIC CHARACTERISTICS AT HIGH 
SPEEDS OF RELATED FULL-SCALE PROPELLERS 
HAVING DIFFERENT BLADE -SECTION CAMBERS. 
Julian D. Maynard and LelandB. Salters, Jr. 1957. 
ii, 24p. diagrs., photos., tab. (NACA Rept. 1309. 
Supersedes RM L8E06) 



AN INVESTIGATION OF SINGLE- AND DUAL- 
ROTATION PROPELLERS AT POSITIVE AND 
NEGATIVE THRUST, AND IN COMBINATION WITH 
AN NACA 1 -SERIES D-TYPE COWLING AT MACH 
NUMBERS UP TO 0.84. Robert M. Reynolds, 
Robert I. Sammonds, and John H. Walker. 1957. 
ii, 58p. diagrs., photos., tabs. (NACA Rept. 1336) 



FLIGHT INVESTIGATION OF A SUPERSONIC PRO- 
PELLER ON A PROPELLER RESEARCH VEHICLE 
AT MACH NUMBERS TO 1.01. Jerome B. 
Hammack, Max C. Kurbjun, and Thomas C. 
O'Bryan. July 1957. 43p. diagrs., photos. 
(NACA RM L57E20) 



EYFECTS OF BLADE PLAN FORM ON FREE- 
SPACE OSCILLATING PRESSURES NEAR PROPEL- 
LERS AT FLIGHT MACH NUMBERS TO 0.72. Max 
C. Kurbjun. August 1957. 20p. diagrs., photos., 
tabs. (NACA TN 4068) 



FLIGHT MEASUREMENTS OF THE VIBRATORY 
BENDING AND TORSIONAL STRESSES ON A 
MODIFIED SUPERSONIC PROPELLER FOR FOR- 
WARD MACH NUMBERS UP TO 0.95. Thomas C. 
O'Bryan. June 1958. 17p. diagrs., photos. 
(NACA TN 4342) 



EFFECT OF ADVANCE RATIO ON FT JGHT PER- 
FORMANCE OF A MODIFIED SUPERSONIC PRO- 
PELLER. Jerome B. Hammack and Thomas C. 
O'Bryan. September 1958. 20p. diagrs., photos. 
(NACA TN 4389) 



FLIGHT MEASUREMENTS OF THE VIBRATORY 
STRESSES ON A PROPELLER DESIGNED FOR AN 
ADVANCE RATIO OF 4 .0 AND A MACH NUMBER 
OF 0.82. Thomas C. O'Bryan. September 1958. 
14p. diagrs., photos. (NACA TN 4410) 



(1.5.2.7) 
DUAL ROTATION 



THE EFFECT OF AN OPERATING PROPELLER ON 
THE AERODYNAMIC CHARACTERISTICS AT HIGH 
SUBSONIC SPEEDS OF A MODEL OF A VERTICAL- 
RISING AIRPLANE HAVING AN UNSWEPT WING OF 
ASPECT RATIO 3. Fred B. Sutton and Donald A. 
Buell. November 1954. 90p. diagrs,, photos., 
tabs. (NACA RM A52E06) 



100 



( 1 ) AERODYNAMICS 



AN INVESTIGATION OF SINGLE- AND DUAL- 
ROTATION PROPELLERS AT POSITIVE AND 
NEGATIVE THRUST, AND IN COMBINATION WITH 
AN NACA 1 -SERIES D-TYPE COWLING AT MACH 
NUMBERS UP TO 0.84. Robert M. Reynolds, 
Robert I. Sammonds, and John H. Walker. 1957. 
ii, 58p. diagrs., photos., tabs. (NACA Rept. 1336) 



(1.5.2.8) 
INTERFERENCE OF B6DIES 



INVESTIGATION OF THE NORMAL FORCE 
ACCOMPANYING THRUST-AXIS INCLINATION OF 
THE NACA 1.167-(0)(03)-058 AND THE NACA 
1.167-(0)(05)-058 THREE-BLADE PROPELLERS AT 
FORWARD MACH NUMBERS TO 0.90. Fred A. 
Deraele and William R. Otey. June 1954. 31p. 
diagrs., photo., tab. (NACA RM A54D22) 



AN INVESTIGATION OF SINGLE- AND DUAL- 
ROTATION PROPELLERS AT POSITIVE AND 
NEGATIVE THRUST, AND IN COMBINATION WITH 
AN NACA 1-SERIES D-TYPE COWLING AT MACH 
NUMBERS UP TO 0.84. Robert M. Reynolds, 
Robert I. Sammonds, and John H. Walker. 1957. 
ii, 58p. diagrs., photos., tabs. (NACA Rept. 1336) 



PRELIMINARY INVESTIGATION OF THE CHAR- 
ACTERISTICS OF A TWO-DIMENSIONAL WING AND 
PROPELLER WITH THE PROPELLER PLANE OF 
ROTATION IN THE WING -CHORD PLANE. David 
H. Hickey. August 1957. 12p. diagrs. 
(NACA RM A57F03) 



LOW-SPEED EXPERIMENTAL INVESTIGATION OF 
THE MAGNUS EFFECT ON VARIOUS SECTIONS OF 
A BODY OF REVOLUTION WITH AND WITHOUT A 
PROPELLER. M. J. Queijo and Herman S. 
Fletcher. August 1957. 68p. diagrs., photos., tab. 
(NACA TN 4013) 



EXPERIMENTAL INVESTIGATION OF THE DRAG 
OF FLAT PLATES AND CYLINDERS IN THE SLIP- 
STREAM OF A HOVERING ROTOR. John W. McKee 
and Rodger L, Naeseth. April 1958. 42p. diagrs., 
photos., tab. (NACA TN 4239) 



(1.5.2.9) 
PITCH AND YAW 



INVESTIGATION OF THE NORMAL FORCE 
ACCOMPANYING THRUST-AXIS INCLINATION OF 
THE NACA l.l67-(0){03)-058 AND THE NACA 
1.167-(0)(05)-058 THREE-BLADE PROPELLERS AT 
FORWARD MACH NUMBERS TO 0.90. Fred A. 
Demele and William R. Otey. June 1954. 31p. 
diagrs., photo., tab. (NACA RM A54D22) 



THE EFFECT OF AN OPERATING PROPELLER ON 
THE AERODYNAMIC CHARACTERISTICS AT HIGH 
SUBSONIC SPEEDS OF A MODEL OF A VERTICAL- 
RISING AIRPLANE HAVING AN UNSWEPT WING OF 
ASPECT RATIO 3. Fred B. Sutton and Donald A. 
Buell. November 1954. 90p. diagrs., photos., 
tabs. (NACA RM A52E06) 



A WIND-TUNNEL INVESTIGATION OF THE FIRST- 
ORDER VIBRATORY STRESSES ON A FULL-SCALE 
SUPERSONIC-TYPE PROPELLER OPERATING IN 
AN ASYMMETRIC AIR FLOW. Atwood R. Heath, 
Jr., and Robert L. O'Neal. November 1954. 28p. 
diagrs., photo. (NACA RM L54B17a) 



LOW-SPEED EXPERIMENTAL INVESTIGATION OF 
THE MAGNUS EFFECT ON VARIOUS SECTIONS OF 
A BODY OF REVOLUTION WITH AND WITHOUT A 
PROPELLER. MJ. Queijo and Herman S. 
Fletcher. August 1957. 68p. diagrs., photos., tab. 
(NACA TN 4013) 



(1.5.3) 
DESIGNATED TYPES 



WAKE SURVEYS IN THE SLIPSTREAM OF A FULL- 
SCALE SUPERSONIC-TYPE THREE-BLADE 
PROPELLER AT MACH NUMBERS TO 0.96. John 
M. Swihart and Harry T. Norton, Jr. October 1953. 
33p. diagrs., photo. (NACA RM L53I09) 



MEASUREMENT AND CALCULATION OF BLADE 
TORSIONAL DEFLECTION OF THREE SUPERSONIC- 
TYPE PROPELLERS. Arthur E. Allis and Willard E. 
Foss, Jr. May 1954. 35p. diagrs., photos. 
(NACA RM L53I16) 



THE EFFECT OF AN OPERATING PROPELLER ON 
THE AERODYNAMIC CHARACTERISTICS AT HIGH 
SUBSONIC SPEEDS OF A MODEL OF A VERTICAL- 
RISING AIRPLANE HAVING AN UNSWEPT WING OF 
ASPECT RATIO 3. Fred B, Sutton and Donald A. 
Buell. November 1954. 90p. diagrs., photos., 
tabs. (NACA RM A52E06) 



FLIGHT MEASUREMENTS OF SECTION EFFI- 
CIENCY, THRUST, AND POWER OF A SUPERSONIC- 
TYPE PROPELLER AT MACH NUMBERS TO 0.9. 
Jerome B. Hammack and Thomas C. O' Bryan. 
January 1956. 38p. diagrs., photos., tab. 
(NACA RM L55I21) 



FLIGHT MEASUREMENTS OF THE VIBRATORY 
BENDING AND TORSION STRESS ON A 
SUPERSONIC-TYPE PROPELLER FOR FLIGHT 
MACH NUMBERS UP TO 0.95. Thomas C. O' Bryan. 
July 1956. 22p. diagrs., photos., tab. 
(NACA RM L56D20a) 



AN INVESTIGATION OF SINGLE- AND DUAL- 
ROTATION PROPELLERS AT POSITIVE AND 
NEGATIVE THRUST, AND IN COMBINATION WITH 
AN NACA 1-SERIES D-TYPE COWLING AT MACH 
NUMBERS UP TO 0.84. Robert M. Reynolds, 
Robert I. Sammonds, and John H. Walker. 1957. 
ii, 58p. diagrs., photos., tabs. (NACA Rept. 1336) 



FLIGHT MEASUREMENTS OF THE VIBRATORY 
BENDING AND TORSIONAL STRESSES ON A 
MODIFIED SUPERSONIC PROPELLER FOR FOR- 
WARD MACH NUMBERS UP TO 0.95. Thomas C. 
O'Bryan. June 1958. 17p. diagrs., photos. 
(NACA TN 4342) 



FLIGHT MEASUREMENTS OF THE VIBRATORY 
STRESSES ON A PROPELLER DESIGNED FOR AN 
ADVANCE RATIO OF 4 .0 AND A MACH NUMBER 
OF 0.82. Thomas C O'Bryan. September 1958. 
14p. diagrs., photos. (NACA TN 4410) 



(1.5.4) 
SLIPSTREAM 



WAKE SURVEYS IN THE SLIPSTREAM OF A FULL- 
SCALE SUPERSONIC-TYPE THREE-BLADE 
PROPELLER AT MACH NUMBERS TO 0.96. John 
M. Swihart and Harry T. Norton, Jr. October 1953. 
33p. diagrs., photo. (NACA RM L53I09) 



(1) AERODYNAMICS 



101 



FLIGHT MEASUREMENTS OF SECTION EFFI- 
CIENCY, THRUST, AND POWER OF A SUPERSONIC- 
TYPE PROPELLER AT MACH NUMBERS TO 0-9. 
Jerome B. Hammack and Thomas C. O'Bryan. 
January 1956. 38p. diagrs., photos., tab. 
(NACA RM L 5 5121) 



FLIGHT INVESTIGATION OF A SUPERSONIC PRO- 
PELLER ON A PROPELLER RESEARCH VEHICLE 
AT MACH NUMBERS TO 1.01. Jerome B. 
Hammack, Max C. Kurbjun, and Thomas C. 
O'Bryan. July 1957. 43p. diagrs., photos. 
(NACA RM L57E20) 



EFFECT OF GROUND PROXIMITY ON THE AERO- 
DYNAMIC CHARACTERISTICS OF A FOUR-ENGINE 
VERTICAL-TAKE -OFF-AND-LANDING 
TRANSPORT-AIRPLANE MODEL WITH TILTING 
WING AND PROPELLERS. William A. Newsom, 
Jr. October 1957. 15p. diagrs., photo., tab. 
(NACA TN 4124) 



INVESTIGATION OF THE EFFECTS OF PRO- 
PELLER DIAMETER ON THE ABILITY OF A 
FLAPPED WING, WITH AND WITHOUT 
BOUNDARY- LAYER CONTROL, TO DEFLECT A 
PROPELLER SLIPSTREAM DOWNWARD FOR 
VERTICAL TAKE-OFF. Kenneth P. Spreemann. 
December 1957. 47p. diagrs., photos. 
(NACA TN 4181) 



EXPERIMENTAL INVESTIGATION OF THE 
LATERAL TRIM OF A WING-PROPELLER COM- 
BINATION AT ANGLES OF ATTACK UP TO 90° 
WITH ALL PROPELLERS TURNING IN THE SAME 
DIRECTION. William A. Newsom, Jr. January 
1958. 27p. diagrs. (NACA TN 4190) 



EFFECTIVENESS OF BOUNDARY- LAYER CON- 
TROL, OBTAINED BY BLOWING OVER A PLAIN 
REAR FLAP IN COMBINATION WITH A FORWARD 
SLOTTED FLAP, IN DEFLECTING A SLIPSTREAM 
DOWNWARD FOR VERTICAL TAKE-OFF. 
Kenneth P. Spreemann. February 1958. 32p. 
diagrs., photo. (NACA TN 4200) 



EXPERIMENTAL INVESTIGATION OF THE DRAG 
OF FLAT PLATES AND CYLINDERS IN THE SLIP- 
STREAM OF A HOVERING ROTOR. John W. McKee 
and Rodger L. Naeseth. April 1958. 42p- diagrs., 
photos., tab. (NACA TN 4239) 



NORMAL COMPONENT OF INDUCED VELOCITY 
FOR ENTIRE FIELD OF A UNIFORMLY LOADED 
LIFTING ROTOR WITH HIGHLY SWEPT WAKE AS 
DETERMINED BY ELECTROMAGNETIC ANALOG. 
Walter Castles, Jr., Howard L. Durham, Jr., and 
Jirair Kevorkian, Georgia Institute of Technology. 
June 1958. 33p. diagrs., photos., tabs. 
(NACA TN 4238) 



EFFECT OF ADVANCE RATIO ON FLIGHT PER- 
FORMANCE OF A MODIFIED SUPERSONIC PRO- 
PELLER. Jerome B. Hammack and Thomas C. 
O'Bryan. September 1958. 20p. diagrs., photos. 

(NACA TN 4389) 



LARGE-SCALE WIND-TUNNEL TESTS OF AN AIR- 
PLANE MODEL WITH AN UNSWEPT, ASPECT- 
RATIO- 10 WING, TWO PROPELLERS, AND AREA - 
fUCTION FLAPS, James A. Weiberg, Roy N. 
Griffin, Jr., and George L. Florman. September 
1958. 76p. diagrs., photos., tab. (NACA TN 4365) 



EFFECTS OF PROPELLER POSITION AND OVER- 
LAP ON THE SLIPSTREAM DEFLECTION CHAR- 
ACTERISTICS OF A WING-PROPELLER CONFIG- 
URATION EQUD?PED WITH A SLIDING AND 
FOWLER FLAP. William C. Hayes, Jr., Richard E. 
Kuhn, and Irving R. Sherman. September 1958. 
81p. diagrs., photos. (NACA TN 4404) 



(1.5.6) 
OPERATING CONDITIONS 



WAKE SURVEYS IH THE SLIPSTREAM OF A FULL- 
SCALE SUPERSONIC -TYPE THREE -BLADE 
PROPELLER AT MACH NUMBERS TO 0.96. John 
M. Swihart and Harry T. Norton, Jr. October 1953. 
33p. diagrs., photo. (NACA RM L53I09) 



ANALYTICAL,**!) EXPERIMENTAL STUDY OF 
TRANSIENT-RESPONSE CHARACTERISTICS OF A 
TURBOPROP ENGINE. R. T. Craig, S. Nakanishi, 
andD. B. Wile. October 1955. 50p. diagrs., photo., 
tabs. (NACA RM E55C23) 



EFFECT OF BLADE-SECTION CAMBER ON AERO- 
DYNAMIC CHARACTERISTICS OF FULL-SCALE 
SUPERSONIC-TYPE PROPELLERS AT MACH NUM- 
BERS TO 1.04. Julian D. Maynard, John M. Swihart, 
and Harry T. Norton, Jr. October 1956. 79p. 
diagrs., photos., tab. (NACA RM L56E10) 



AERODYNAMIC CHARACTERISTICS AT HIGH 
SPEEDS OF RELATED FULL-SCALE PROPELLERS 
HAVING DIFFERENT BLADE -SECTION CAMBERS. 
Julian D. Maynard and LelandB. Salters, Jr. 1957. 
ii, 24p. diagrs., photos., tab. (NACA Rept. 1309. 
Supersedes RM L8E06) 



FLIGHT INVESTIGATION OF A SUPERSONIC PRO- 
PELLER ON A PROPELLER RESEARCH VEHICLE 
AT MACH NUMBERS TO 1.01. Jerome B. 
Hammack, Max C. Kurbjun, and Thomas C. 
O'Bryan. July 1957. 43p. diagrs., photos. 
(NACA RM L57E20) 



PRELIMINARY INVESTIGATION OF THE CHAR- 
ACTERISTICS OF A TWO-DIMENSIONAL WING AND 
PROPELLER WITH THE PROPELLER PLANE OF 
ROTATION IN THE WING-CHORD PLANE . David 
H. Hickey. August 1957. 12p. diagrs. 
(NACA RM A57F03) 



EFFECT OF ADVANCE RATIO ON FLIGHT PER- 
FORMANCE OF A MODIFIED SUPERSONIC PRO- 
PELLER. Jerome B. Hammack and Thomas C. 
O'Bryan. September 1958. 20p. diagrs., photos. 
(NACA TN 4389) 



(1.5.7) 
PROPELLER - SPINNER - COWL 
COMBINATIONS 



AN INVESTIGATION OF SINGLE- AND DUAL- 
ROTATION PROPELLERS AT POSITIVE AND 
NEGATIVE THRUST, AND IN COMBINATION WITH 
AN NACA 1-SERIES D-TYPE COWLING AT MACH 
NUMBERS UP TO 0.84. Robert M. Reynolds, 
Robert L Sammonds, and John H. Walker, 1957. 
ii, 58p. diagrs., photos., tabs. (NACA Rept. 1336) 



102 



(1) AERODYNAMICS 



FLIGHT INVESTIGATION OF A SUPERSONIC PRO- 
PELLER ON A PROPELLER RESEARCH VEHICLE 
AT MACH NUMBERS TO 1.01. Jerome B, 
Hammack, Max C. Kurbjun, and Thomas C. 
O'Bryan. July 1957. 43p. dlagrs., photos. 
(NACA RM L57E20) 



EFFECT OF ADVANCE RATIO ON FLIGHT PER- 
FORMANCE OF* A MODIFIED SUPERSONIC PRO- 
PELLER. Jerome B. Hammack and Thomas C. 
O'Bryan. September 1958. 20p. dlagrs., photos. 
(NACA TN 4389) 



103 



(1) AERODYNAMICS 



0*6) 
Rotating Wings 



(1.6.1) 
THEORY 



EXPERIMENTAL INVESTIGATION OF THE AERO- 
DYNAMIC LOADING ON A HELICOPTER ROTOR 
BLADE IN FORWARD FLIGHT. John P. Rabbott, 
Jr., and Gary B. Churchill. October 1956. 65p. 
diagrs., photos., tabs. (NACA RM L 56107) 



INDUCED VELOCITIES NEAR A LIFTING ROTOR 
WITH NONUNIFORM DISK LOADING. Harry H. 
Hey son and S. Katzotf. 1957. Ill, 8Bp. dlagrs., 
photos., tab. (NACA Rept. 1319. Supersedes 
TN 3690; TN 3691) 



ANALYSIS OF HARMONIC FORCES PRODUCED AT 
HUB BY IMBALANCES IN HELICOPTER ROTOR 
BLADES. M. Morduchow and A. Muzyka, 
Polytechnic Institute of Brooklyn. April 1958. 37p. 
diagrs. (NACA TN 4226) 



NORMAL COMPONENT OF INDUCED VELOCITY 
FOR ENTIRE FIELD OF A UNIFORMLY LOADED 
LIFTING ROTOR WITH HIGHLY SWEPT WAKE AS 
DETERMINED BY ELECTROMAGNETIC ANALOG. 
Walter Castles, Jr., Howard L. Durham, Jr., and 
Jlrair Kevorkian, Georgia Institute of Technology. 
June 1958. 33p. dlagrs., photos., tabs. 
(NACA TN 4238) 



(1.6.2) 
EXPERIMENTAL STUDIES 



EXPERIMENTAL INVESTIGATION OF THE AERO- 
DYNAMIC LOADING ON A HELICOPTER ROTOR 
BLADE IN FORWARD FLIGHT. John P. Rabbott, 
Jr., and Gary B. Churchill. October 1956. 65p. 
diagrs., photos., tabs. (NACA RM L56I07) 



FLIGHT AND ANALYTICAL METHODS FOR DETER- 
MINING THE COUPLED VIBRATION RESPONSE OF 
TANDEM HELICOPTERS. John E. Yeates t Jr., 
George W. Brooks, and John C. Houbolt. 1957. iv, 
31p. diagrs., photo., tabs. (NACA Rept. 1326. 
Supersedes TN 3852: TN 3*49) 



FLIGHT INVESTIGATION OF EFFECTS OF ATMOS- 
PHERIC TURBULENCE AND MODERATE MANEU- 
VERS ON BENDING AND TORSIONAL MOMENTS 
ENCOUNTERED BY A HELICOPTER ROTOR BLADE. 
LeRoy H. Ludi. February 1958. 34p. dlagrs., 
photo., tab. (NACA TN 4203) 



EXPERIMENTAL INVESTIGATION OF THE DRAG 
OF FLAT PLATES AND CYLINDERS IN THE SLIP- 
STREAM OF A HOVERING ROTOR. John W. McKee 
and Rodger L. Naeseth. April 1958. 42p. dlagrs., 
photos., tab. (NACA TN 4239) 



FLIGHT INVESTIGATION OF EFFECTS OF 
RETREATING-BLADE STALL ON BENDING AND 
TORSIONAL MOMENTS ENCOUNTERED BY A 
HELICOPTER ROTOR BLADE. LeRoy H. Ludi. 
May 1958. 23p. diagrs., photo. (NACA TN 4254) 



AN EXPERIMENTAL INVESTIGATION OF THE 
EFFECT OF VARIOUS PARAMETERS INCLUDING 
TIP MACH NUMBER ON THE FLUTTER OF SOME 
MODEL HELICOPTER ROTOR BLADES. George W. 
Brooks and John E. Baker. September 1958. 68p. 
diagrs., photo., tabs. (NACA TN 4005. Supersedes 
RM L53D24) 



WIND-TUNNEL TESTS OF A FULL-SCALE HELI- 
COPTER ROTOR WITH SYMMETRICAL AND WITH 
CAMBERED BLADE SECTIONS AT ADVANCE 
RATIOS FROM 0.3 TO 0.4. John L. McCloud UJ and 
George B. McCullough. September 1958. 33p. 
diagrs., photos., tab. (NACA TN 4367) 



FLIGHT MEASUREMENTS'OF THE VIBRATION 
EXPERIENCED BY A TANDEM HELICOPTER IN 
TRANSITION, VORTEX-RING STATE, LANDING 
APPROACH, AND YAWED FLIGHT. John E . Yeates. 
September 1956. 20p. dlagrs. (NACA TN 4409) 



(1.6.2. 1) 
POWER DRIVEN 



INDUCED VELOCITIES NEAR A LIFTING ROTOR 
WITH NONUNIFORM DISK LOADING. Harry H. 
Hey son and S. Katzoff. 1957. Hi, 88p. diagrs., 
photos., tab. (NACA Rept. 1319. Supersedes 
TN 3690; TN 3691) 



COMPRESSIBILITY EFFECTS ON A HOVERING 
HELICOPTER ROTOR HAVING AN NACA 0018 ROOT 
AIRFOIL TAPERING TO AN NACA 0012 TIP AIR- 
FOIL. Robert D. Powell, Jr. September 1957. 
25p. diagrs. (NACA RM L57F26) 



LOW TIP MACH NUMBER STALL CHARACTERIS- 
TICS AND HIGH TIP MACH NUMBER COMPRESSI- 
BILITY EFFECTS ON A HELICOPTER ROTOR 
HAVING AN NACA 0009 TIP AIRFOIL SECTION. 
Robert D. Powell, Jr., and Paul J. Carpenter. July 
1958. 28p. diagrs. (NACA TN 4355) 



EFFECTS OF COMPRESSIBILITY ON ROTOR HOV- 
ERING PERFORMANCE AND SYNTHESIZED BLADE - 
SECTION CHARACTERISTICS DERIVED FROM 
MEASURED ROTOR PERFORMANCE OF BLADES 
HAVING NACA 0015 AIRFOIL TD? SECTIONS. 
James P. Shivers and Paul J. Carpenter. September 
1958. 28p. diagrs. (NACA TN 4356) 



LIFT AND PROFILE-DRAG CHARACTERISTICS OF 
AN NACA 0012 AIRFOIL SECTION AS DERIVED 
FROM MEASURED HELICOPTER-ROTOR HOVER- 
ING PERFORMANCE. Paul J. Carpenter. 
September 1958. 28p. dlagrs., photo. 
(NACA TN 4357) 



WIND-TUNNEL TESTS OF A FULL-SCALE HELI- 
COPTER ROTOR WITH SYMMETRICAL AND WITH 
CAMBERED BLADE SECTIONS AT ADVANCE 
RATIOS FROM 0.3 TO 0.4. John L. McCloud m and 
George B. McCullough. September 1958. 33p. 
diagrs., photos., tab. (NACA TN 4367) 



104 

( 1 ) AERODYNAMICS 



(1.6.2.2) 
AUTOROTATING 



FULL-SCALE WIND-TUNNEL TESTS OF THE LON- 
GITUDINAL STABILITY AND CONTROL CHARAC- 
TERISTICS OF THE XV- 1 CONVERTIPLANE IN THE 
AUTOROTATING FLIGHT RANGE. David H. Hickey. 
May 1956. 64p. diagrs., photos., tabs. 
(NACA RM A55K21a) 



105 



(1) AERODYNAMICS 



(1.7) 
Aircraft 



(1.7.1) 
AIRPLANES 



LOW-SPEED STATIC LONGITUDINAL AND LAT- 
ERAL STABILITY CHARACTERISTICS OF A MODEL 
WITH LEADING- EDGE CHORD-EXTENSIONS INCOR- 
PORATED ON A 40O SWEPTBACK CIRCULAR-ARC 
WING OF ASPECT RATIO 4 AND. TAPER RATIO 0.50. 
Kenneth W. Goodson and Albert G. Few, Jr. 
November 1952. 46p. diagrs., photos., tab. 
(NACA RM L52I18) 



STATUS OF SPIN RESEARCH FOR RECENT AIR- 
PLANE DESIGNS. Anshal I. Neihouse, Salter J. 
Klinar, and Stanley H. Scher. August 1957. ii, 
98p. diagrs., photos., tabs. (NACA RM L57F12) 



(1.7.1.1) 
COMPONENTS IN COMBINATION 



ESTIMATED TRANSONIC FLYING QUALITIES OF A 
TAILLESS AIRPLANE BASED ON A MODEL INVES- 
TIGATION. Charles J. Donlan and Richard E. Kuhn. 
June 8, 1949. 03p. diagrs., photos., tabs. 
(NACA RM L9D08) 



LARGE-SCALE FLIGHT MEASUREMENTS OF 
ZERO-LIFT DRAG AT MACH NUMBERS FROM 0.90 
TO 1.95 OF AN ARROW WING IN COMBINATION 
WITH A SMALL BODY. Warren Gillespie, Jr., and 
Richard G. Arbic. January 12, 1951. 17p. diagrs., 
photos., tab. (NACA RM L50K28a) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR-ARC SECTIONS AND 40° SWEEPBACK. 
FORCE CHARACTERISTICS OF THE COMPLETE 
CONFIGURATION AND ITS VARIOUS COMPONENTS 
AT MACH NUMBERS OF 1.40 AND 1.59. Norman F. 
Smith and Jack E. Marte. January 22, 1951. 55p. 
diagrs., photos., tab. (NACA RM L50K14) 



WING-ON AND WING-OFF LONGITUDINAL CHAR- 
ACTERISTICS OF AN AIRPLANE CONFIGURATION 
HAVING A THIN UNSWEPT TAPERED WING OF 
ASPECT RATIO 3, AS OBTAINED FROM ROCKET- 
PROPELLED MODELS AT MACH NUMBERS FROM 
0.8 TO 1.4. Clarence L. Gillis and A. James Vitale. 
March 14, 1951. 52p. diagrs., photos., tabs. 
(NACA RM L50K16) 



DIVISION OF LOAD AMONG THE WING, FUSELAGE, 
AND TAIL OF AIRCRAFT. John P. Mayer and 
Clarence L. Gillis. May 29, 1951. 14p. diagrs. 
(NACA RM L51E14a) 



LONGITUDINAL STABILITY AND DRAG CHARAC- 
TERISTICS AT MACH NUMBERS FROM 0.75 TO 1.5 
OF AN AIRPLANE CONFIGURATION HAVING A 60° 
SWEPT WING OF ASPECT RATIO 2.24 AS OB- 
TAINED FROM ROCKET-PROPELLED MODELS. 
A. James Vitale, John C. McFall, Jr., and John D. 
Morrow. April 1952. 43p. diagrs., photos., tabs. 
(NACARM L51K06) 



LONGITUDINAL AERODYNAMIC CHARACTERISTICS 
OF MODEL AIRPLANE CONFIGURATTON EQUIPPED 
WITH A SCALED X-l AIRPLANE WING. Jamas H. 
Parks. April 1952. 37p. diagrs. 
(NACA RM L5lL10a) 



LARGE-SCALE FLIGHT MEASUREMENTS OF 
ZERO-LIFT DRAG OF 10 WING-BODY CONFIGURA- 
TIONS AT MACH NUMBERS FROM 0.8 TO 1.8. 
John D. Morrow and Robert L. Nelson. January 
1953. 53p. diagrs., photo., tabs. 
(NACA RM L52D18a) 



INVESTIGATION OF THE EFFECT OF SPANWBE 
POSITIONING OF A VERTICALLY SYMMETRIC 
OGIVE -CYLINDER NACELLE ON THE HIGH-SPEED 
AERODYNAMIC CHARACTERISTICS OF A 45° 
SWEPTBACK TAPERED-IN-THICKNESS WING OF 
ASPECT RATIO 6 WITH AND WITHOUT A FUSE- 
LAGE. H. Norman Silvers and Thomas J. King, Jr. 
October 1953. 62p. diagrs., tabs. 
(NACA RM L53H17) 



LONGITUDINAL STABILITY CHARACTERISTICS 
AT TRANSONIC SPEEDS OF A ROCKET- 
PROPELLED MODEL OF AN AIRPLANE CON- 
FIGURATION HAVING A 450 SWEPT WING OF 
ASPECT RATIO 6.0. John C. McFall, Jr. 
January 1954. S4p, diagrs., photo*. 
(NACA RM L5SG22*.) 



AERODYNAMIC CHARACTERISTICS AT TRANSONIC 
AND SUPERSONIC SPEEDS OF A ROCKET- 
PROPELLED AIRPLANE CONFIGURATION HAVING 
A 52.50 DELTA WING AND A LOW, SWEPT HORI- 
ZONTAL TAIL. Alan B. Kehlet. March 1954, 31p. 
diagrs., photos. (NACA RM L54A20) 



THE EFFECTS OF WING-MOUNTED EXTERNAL 
STORES ON THE TRIM, BUFFET, AND DRAG 
CHARACTERISTICS OF A ROCKET -PROPELLED 
MODEL HAVING A 45° SWEPTBACK WING. Allen B. 
Henning. April 1954. 25p. diagrs., photos., tabs. 
(NACARML54B19) 



LIFT AND DRAG CHARACTERISTICS OF THE 
DOUGLAS D-558-II RESEARCH AIRPLANE OB- 
TAINED IN EXPLORATORY FLIGHTS TO A MACH 
NUMBER OF 2.0. Jack Nugent. August 1954. 20p. 
diagrs., photo., tab. (NACA RM L54F03) 



STABILITY AND DRAG CHARACTERISTICS AT 
MACH NUMBERS FROM 0.8 TO 1.5 OF A FREE- 
FLIGHT MODEL HAVING 3-PERCENT-THICK, 600 
TRIANGULAR WING AND HORIZONTAL TAIL SUR- 
FACES. Row e Chapman, Jr., and Harvey A. ' 
Wallsteog. August 1954. 3 Op. diagrs., photos., tab. 
(NACA RM L54G23a) 



AERODYNAMIC CHARACTERISTICS AT TRANSONIC 
AND SUPERSONIC SPEEDS OF A ROCKET- 
PROPELLED AIRPLANE CONFIGURATION HAVING 
A DIAMOND-PLAN-FORM WING OF ASPECT RATIO 
3.08 AND A LOW, SWEPT HORIZONTAL TAIL. 
Alan B. Kehlet. September 1954. 37p. diagrs., 
photos. (NACA RM L54G27a) 



106 



(1) AERODYNAMICS 



LONGITUDINAL STABILITY CHARACTERISTICS AT 
TRANSONIC SPEEDS OF A CANARD CONFIGURA- 
TION HAVING A 45° SWEPTBACK WING OF ASPECT 
RATIO 6.0 AND NACA 65A009 AIRFOIL SECTION. 
A. James Vitale and John C. McFall, Jr. November 
1954. 24p. diagrs., photos., tab. 
(NACA RM L54I01) 



LATERAL MOTIONS ENCOUNTERED WITH THE 
DOUGLAS D-558-II ALL-ROCKET RESEARCH AIR- 
PLANE DURING EXPLORATORY FLIGHTS TO A 
MACH NUMBER OF 2.0. Herman O. Ankenbruck 
and Chester H. Wolowicz. December 1954. 32p. 
diagrs., photos., tab. (NACA RIvI H54I2T) 



EFFECTS OF SOME EXTERNAL-STORE MOUNTING 
ARRANGEMENTS AND STORE SHAPES ON THE 
BUFFET AND DRAG CHARACTERISTICS OF WING- 
LESS ROCKET-POWERED MODELS AT MACH NUM- 
BERS FROM 0.7 TO 1.4. Homer P. Mason and 
Allen B. Henning. December 1954. 45p. diagrs., 
photos., tabs. (NACA RM L54I20a) 



JET EFFECTS ON LONGITUDINAL TRIM OF AN 
AIRPLANE CONFIGURATION MEASURED AT MACH 
NUMBERS BETWEEN 1.2 AND 1.8. Robert F. Peck. 
January 1955. 17p. diagrs., photos. 
(NACARM L54j29a) 



TRANSONIC LONGITUDINAL AERODYNAMIC 
EFFECTS OF SWEEPING UP THE REAR OF THE 
FUSELAGE OF A ROCKET-PROPELLED AIR- 
PLANE MODEL HAVING NO HORIZONTAL TAIL. 
James H. Parks. January 1955. 3 Op. diagrs., 
photo. (NACA RM L54K12) 



A THEORETICAL INVESTIGATION OF THE EF- 
FECT OF AUXILIARY DAMPING ON THE LONGI- 
TUDINAL RESPONSE OF A TRANSONIC BOMBER 
CONFIGURATION IN FLIGHT THROUGH CON- 
TINUOUS TURBULENCE. T. F. Bridgland, Jr. 
March 1955. 26p. diagrs., tab. 
(NACA RM L54K15a) 



PRELIMINARY RESULTS FROM FLIGHT MEASURE- 
MENTS IN GRADUAL-TURN MANEUVERS OF THE 
WING LOADS AND THE DISTRIBUTION OF LOAD 
AMONG THE COMPONENTS OF A BOEING B-47A 
AIRPLANE. T. V. Cooney, William H- Andrews, 
and William A. McGowan. June 1955. 20p. diagrs., 
photo., tab. (NACA RM L55B02) 



LONGITUDINAL CHARACTERISTICS AT TRANSONIC 
AND SUPERSONIC SPEEDS OF A ROCKET- 
PROPELLED AIRPLANE MODEL HAVING A 60° 
DELTA WING AND A LOW SWEPT HORIZONTAL 
TAIL. Robert F. Peck and Lucille C. Coltrane. 
September 1955. 33p. diagrs., photo., tabs. 
(NACA RM L55F27) 



A FREE-FLIGHT INVESTIGATION OF THE DRAG 
COEFFICIENTS OF TWO SINGLE -ENGINE SUPER- 
SONIC INTERCEPTOR CONFIGURATIONS FROM 
MACH NUMBER 0.8 TO 1.90 TO DETERMINE THE 
EFFECT OF INLET AND ENGINE LOCATION. 
APPENDLX; SEPARATION CHARACTERISTICS OF 
A MODEL FROM A LARGE UNDERSLUNG BOOSTER 
AT MACH NUMBER 1.95. Joseph H. Judd. 
September 1955. 49p. diagrs., photos., tabs. 
(NACA RM L55G05a) 



FREE-FLIGHT INVESTIGATION TO OBTAIN DRAG- 
AT-LIFT AND STABILITY DATA FOR A 60° DELTA- 
WING-BODY CONFIGURATION OVER A MACH NUM- 
BER RANGE OF 1.3 TO 1.6. Clement J. Welsh. 
October 1955. 23p. diagrs., photo., tab. 
(NACA RM L55G14) 



WIND-TUNNEL MEASUREMENTS OF THE DYNAMIC 
CROSS DERIVATIVE C, - C z . (ROLLING MO- 



'& 



MENT DUE TO YAWING VELOCITY AND TO AC- 
CELERATION IN SIDESLIP) OF THE DOUGLAS 
D-558-II AIRPLANE AND ITS COMPONENTS AT 
SUPERSONIC SPEEDS INCLUDING DESCRIPTION 
OF THE TECHNIQUE. William B. Boatright. 
November 1955. 57p. diagrs., photos. 
(NACA RM L55H16) 



LONGITUDINAL STABILITY INVESTIGATION FOR 
A MACH NUMBER RANGE OF 0.8 TO 1.7 OF AN 
AIRPLANE CGNFiUURATlON WITH A 4b° SWEPT 
WING AND A LOW HORIZONTAL TAIL. John C. 
McFall, Jr. February 1956. 32p. diagrs.. photos., 
tab. (NACA RM L55L09) 



RESULTS OF ROCKET MODEL TEST OF AN AIR- 
PLANE CONFIGURATION HAVING AN ARROW WING 
AND SLENDER FLAT -SIDED FUSELAGE. LIFT, 
DRAG, LONGITUDINAL STABILITY, LATERAL 
FORCE, AND JET EFFECTS AT MACH NUMBERS 
BETWEEN 1.0 AND 2.3. Robert F. Peck. 
February 1956. 26p. diagrs., photo. 
(NACARM L55L29) 



FREE -FLIGHT INVESTIGATION OF THE CONTROL 
EFFECTIVENESS OF A DIFFERENTIALLY DE- 
FLECTED HORIZONTAL TAIL AT MACH NUMBERS 
FROM 0.8 TO 1.6. Jesse L. Mitchell and A. James 
Vitale. April 1956. 25p. diagrs., photo., tabs. 
(NACA RM L56B20) 



FULL-SCALE WIND-TUNNEL TESTS OF THE LON- 
GITUDINAL STABILITY AND CONTROL CHARAC- 
TERISTICS OF THE XV-1 CONVERTIPLANE IN THE 
AUTOROTATING FLIGHT RANGE. David H. Hickey. 
May 1956. 64p. diagrs., photos., tabs. 
(NACA RM A55K21a) 



FREE-FLIGHT INVESTIGATION OVER A MACH 
NUMBER RANGE FROM 0.74 TO 1.43 AT LIFT CO- 
EFFICIENTS FROM -0.15 TO 0.75 OF AN AIRPLANE - 
CONFIGURATION MODEL HAVING A 52.5° DELTA 
WING AND A LOW SWEPT HORIZONTAL TAIL. 
Alan B. Kehlet. September 1956. 41p. diagrs., 
photos. (NACA RM L56G09) 



AN EXPERIMENTAL STUDY OF THE ZERO- 
ANGLE -OF -ATTACK TRANSONIC DRAG ASSOCI- 
ATED WITH THE VERTICAL POSITION OF A HORI- 
ZONTAL TAIL AT ZERO INCIDENCE. Robert R. 
Howell. October 1956. 21p. diagrs., photos., tab. 
(NACA RM L56H07) 



NONLIFTING WING -BODY COMBINATIONS WITH 
CERTAIN GEOMETRIC RESTRAINTS HAVING 
MINIMUM WAVE DRAG AT LOW SUPERSONIC 
SPEEDS. Harvard Lomax. 1957. ii, lip. diagrs. 
(NACA Rept. 1297. Supersedes TN 3667) 



THEORETICAL AND EXPERIMENTAL INVESTIGA- 
TION OF THE SUBSONIC -FLOW FIELDS BENEATH 
SWEPT AND UNSWEPT WINGS WITH TABLES OF 
VORTEX-INDUCED VELOCITIES. William J. 
Alford, Jr. 1957. ii, 43p. diagrs., photo., tabs. 
(NACA Rept. 1327. Supersedes TN 3738) 



DETERMINATION OF LONGITUDINAL STABILITY 
AND CONTROL CHARACTERISTICS FROM FREE- 
FLIGHT MODEL TESTS WITH RESULTS AT TRAN- 
SONIC SPEEDS FOR THREE AIRPLANE CONFIGU- 
RATIONS. Clarence L. GiUis and Jesse L. Mitchell. 
1957. Ii, 28p. diagrs., photos., tabs. 
(NACA Rept. 1337) 



107 



(1) AERODYNAMICS 



LOW-SPEED EXPERIMENTAL INVESTIGATION OF 
THE MAGNUS EFFECT ON VARIOUS SECTIONS OF 
A BODY OF REVOLUTION WITH AND WITHOUT A 
PROPELLER. M. J. Queijo and Herman S. 
Fletcher. August 1957. 68p. diagrs., photos., tab. 
(NACA TN 4013) 



STATIC LONGITUDINAL AND LATERAL STABILITY 
CHARACTERISTICS AT LOW SPEED OF 45° 
SWEPTBACK-MIDWING MODELS HAVING WINGS 
WITH AN ASPECT RATIO OF 2, 4, OR 6. David F. 
Thomas, Jr., and Walter D. Wolhart. September 
1957. 30p. diagrs., photos., tabs. (NACA TN 4077) 



ACCELERATION IN FIGHTER -AIRPLANE 
CRASHES. Loren W. Acker, Dugald O. Black, and 
Jacob C. Moser. November 1957. 78p. diagrs., 
photos. (NACA RM E57G11) 



A METHOD FOR THE CALCULATION OF THE 
LATERAL RESPONSE OF AIRPLANES TO RANDOM 
TURBULENCE. John M. Eggleston and William H. 
Phillips. February 1958. 34p. diagrs., tab. 
(NACA TN 4196) 



A METHOD FOR THE CALCULATION OF WAVE 
DRAG ON SUPERSONIC-EDGED WINGS AND BI- 
PLANES. Harvard Lomax and Loma Sluder. 
March 1958. 24p. (NACA TN 4232) 



SPECIAL BODIES ADDED ON A WING TO REDUCE 
SHOCK-INDUCED BOUNDARY -LAYER SEPARATION 
AT HIGH SUBSONIC SPEEDS. Richard T. Whitcomb. 
June 1958. 48p. diagrs., photos. (NACA TN 4293) 



SUPERSONIC WAVE INTERFERENCE AFFECTING 
STABILITY. Eugene S. Love. September 1958. 
19p. diagrs., photos. (NACA TN 4358. Supersedes 
RM L55L14a) 



FREE-FLIGHT INVESTIGATION TO DETERMINE 
THE DRAG OF FLAT- AND VEE-WINDSHIELD 
CANOPIES ON A PARABOLIC FUSELAGE WITH 
AND WITHOUT TRANSONIC INDENTATION 
BETWEEN MACH NUMBERS OF 0.75 AND 1.35. 
Walter L. Kouyoumjlan and Sherwood Hoffman. 
September 1958. 34p. diagrs., photos., tabs. 
(NACA TN 4405) 



(1.7.1.1.1) 
Wing -Fuselage 



AERODYNAMIC STUDY OF A WING-FUSELAGE 
COMBINATION EMPLOYING A WING SWEPT BACK 
63°. _ EFFECTS AT SUBSONIC SPEEDS OF A 
CONSTANT-CHORD ELEVON ON A WING CAM- 
BERED AND TWISTED FOR A UNIFORM LOAD AT 
A LIFT COEFFICIENT OF 0.25. J. Lloyd Jones and 
Fred A. Demele. December 5, 1949. 44p. diagrs., 
photos,, tab. (NACA RM A9I27) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR-ARC SECTIONS AND 40° SWEEPBACK. 
A PRESSURE-DISTRIBUTION STUDY OF THE AERO- 
DYNAMIC CHARACTERISTICS OF THE WING AT 
MACH NUMBER 1.59. Morton Cooper and M. Leroy 
Spearman. May 23, 1950. 52p. diagrs., photos., 
tabs. (NACA RM L50C24) 



A COMPARISON OF THE AERODYNAMIC CHARAC- 
TERISTICS AT TRANSONIC SPEEDS OF FOUR 
WING-FUSELAGE CONFIGURATIONS AS DETER- 
MINED FROM DIFFERENT TEST TECHNIQUES 
Charles J. Donlan, BoydC. Myers, II. and Axel T 
Mattson. October 4, 1950 66p diagrs . photos., 
tabs. (NACA RM L5OH02) 



LARGE-SCALE FLIGHT MEASUREMENTS OF 
ZERO-LIFT DRAG, AT MACH NUMBERS FROM 0.90 
TO 1.95 OF AN ARROW WING IN COMBINATION 
WITH A SMALL BODY. Warren Gillespie, Jr., and 
Richard G. Arbic. January 12, 1951. 17p. diagrs., 
photos., tab. (NACA RM L50K28a) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR-ARC SECTION AND 40<> SWEEPBACK. 
A PRESSURE-DISTRD3UTION STUDY OF THE AERO- 
DYNAMIC CHARACTERISTICS OF THE WING AT 
MACH NUMBER 1.40. Norman F. Smith, Julian H. 
Kalner, and Robert A. Webster. April 20, 1951. 
48p. diagrs., photos., tabs. (NACA RM L51C06) 



BASIC PRESSURE MEASUREMENTS ON A FUSE- 
LAGE AND A 45° SWEPTBACK WING-FUSELAGE 
COMBINATION AT TRANSONIC SPEEDS IN THE 
SLOTTED TEST SECTION OF THE LANGLEY 
8-FOOT HIGH-SPEED TUNNEL. Donald L. Loving 
and Claude V. Williams. September 1951. 59p. 
diagrs., photos. (NACA RM L51F05) 



AN INVESTIGATION AT TRANSONIC SPEEDS OF 
THE EFFECTS OF THICKNESS RATIO AND OF 
THICKENED ROOT SECTIONS ON THE AERODY- 
NAMIC CHARACTERISTICS OF WINGS WITH 47° 
SWEEPBACK, ASPECT RATIO 3.5, AND TAPER 
RATIO 0.2 IN THE SLOTTED TEST SECTION OF 
THE LAN OLE V 8 -FOOT HIGH-SPEED TUNNEL. 
Ralph P. Bielat, Daniel E. Harrison, andDomenicA. 
Coppolino. October 1951. 38p. diagrs., photo., tab. 
(NACA RM L5 1104a) 



FLIGHT DETERMINATION OF THE DRAG AND 
LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A ROCKET -POWERED MODEL 
OF A 60° DELTA-WING AIRPLANE FROM MACH 
NUMBERS OF 0.75 TO 1.70. Grady L. Mitcham, 
Norman L. Crabill, and Joseph E. Stevens. 
November 1951. 44p. diagrs., photos., tab. 
(NACA RM L51I04) 



AERODYNAMIC CHARACTERISTICS AT SUPER- 
SONIC SPEEDS OF A SERIES OF WING-BODY 
COMBINATIONS HAVING CAMBERED WINGS WTTH 
AN ASPECT RATIO OF 3.5 AND A TAPER RATIO OF 
0.2. EFFECTS OF SWEEP ANGLE AND THICKNESS 
RATIO ON THE STATIC LATERAL STABILITY 
CHARACTERISTICS AT M = 1.60. M. Leroy 
Spearman and John H. Hilton, Jr. January 1952. 
31 p. diagrs., tabs. (NACA RM L51K15a) 



AERODYNAMIC CHARACTERISTICS AT SUPER- 
SONIC SPEEDS OF A SERIES OF WING-BODY 
COMBINATIONS HAVING CAMBERED WINGS WITH 
AN ASPECT RATIO OF 3.5 AND A TAPER RATIO 
OF 0.2. EFFECTS OF SWEEP ANGLE AND THICK- 
NESS RATIO ON THE AERODYNAMIC CHARACTER- 
ISTICS IN PITCH AT M = 1.60. Ross B. Robinson 
and Cornelius Driver. January 1952. 27p. diagrs., 
photos., tabs. (NACA RM L51K16a) 



THE STATIC AND DYNAMIC LONGITUDINAL SUA- 
BILITY CHARACTERISTICS OF SOME SUPERSONIC 
AIRCRAFT CONFIGURATIONS. Jesse L. Mitchell. 
January 1952. 19p. diagrs. (NACA RM L52A10a) 



AERODYNAMIC LOADING CHARACTERISTICS OF A 
WING-FUSELAGE COMBINATION HAVING A WING 
OF 45° SWEEPBACK MEASURED IN THE LANGLEY 
8-FOOT TRANSONIC TUNNEL. Donald L. Loving 
and Claude V. Williams. May 1952. 58p. diagrs., 
photos . , tab . (NACA RM L 52B27) 



108 



(1) AERODYNAMICS 



A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE AERODYNAMIC CHARACTERISTICS OF THREE 
4-PERCENT -THICK WINGS OF SWEEPBACK 
ANGLES 10.80, 350, AND 47°, ASPECT RATIO 3.5, 
AND TAPER RATIO 0.2 IN COMBINATION WITH A 
BODY. Ralph P. Bielat. July 1952. 33p. dlagrs., 
photos., tab. (NACA RM L52B08) 

AERODYNAMIC CHARACTERISTICS AT SUPER- 
SONIC SPEEDS OF A SERIES OF WING-BODY COM- 
BINATIONS HAVING CAMBERED WINGS WITH AN 
ASPECT RATIO OF 3.5 AND A TAPER RATIO OF 
0.2. EFFECTS OF SWEEP ANGLE AND THICKNESS 
RATIO ON THE AERODYNAMIC CHARACTERISTICS 
IN PITCH AT M = 2.01. Ross B. Robinson. July 
1952. 27p. diagrs., photo., tabs. 
(NACA RM L52E09) 

AERODYNAMIC CHARACTERISTICS AT SUPER- 
SONIC SPEEDS OF A SERIES OF WING-BODY COM- 
BINATIONS HAVING CAMBERED WINGS WITH AN 
ASPECT RATIO OF 3.5 AND A TAPER RATIO OF 
0.2. EFFECTS OF SWEEP ANGLE AND THICKNESS 
RATIO ON THE STATIC LATERAL STABILITY 
CHARACTERISTICS AT M = 2.01. Clyde V. 
Hamilton. August 1952. 37p. diagrs., tabs. 
(NACA RM L52E23) 



INVESTIGATION OF INTERFERENCE LIFT, DRAG, 
AND PITCHING MOMENT OF A SERIES OF REC- 
TANGULAR WING AND BODY COMBINATIONS AT 
MACH NUMBERS OF 1.62, 1.93, AND 2.41. Donald 
E. Coletti. August 1952. 74p. diagrs., tabs. 
(NACA RM L52E26) 



PRELIMINARY INVESTIGATION OF THE LOW- 
AMPLITUDE DAMPING IN PITCH OF TAILLESS 
DELTA- AND SWEPT -WING CONFIGURATIONS AT 
MACH NUMBERS FROM 0.7 TO 1.35. Charles T. 
D*Aiutolo and Robert N. Parker. August 1952. 27p. 
diagrs., photos., tab. (NACA RM L52G09) 



EFFECTS OF WING ELASTICITY ON THE AERO- 
DYNAMIC CHARACTERISTICS OF A 45<> 
SWEPTBACK-WING-FUSELAGE COMBINATION 
MEASURED IN THE LANGLEY 8- FOOT TRANSONIC 
TUNNEL. Robert S. Osborne and John P. Mugler, 
Jr. September 1952. 27p. diagrs., photos. 
(NACA RM L52G23) 



LARGE-SCALE FLIGHT MEASUREMENTS OF 
ZERO-LIFT DRAG OF 10 WING-BODY CONFIGURA- 
TIONS AT MACH NUMBERS FROM 0.8 TO 1.6. 
John D. Morrow and Robert L. Nelson. January 
1953. 53p. diagrs., photo., tabs. 
(NACA RM L52D18a) 

EFFECT OF LEADING-EDGE CHORD-EXTENSIONS 
ON SUBSONIC AND TRANSONIC AERODYNAMIC 
CHARACTERISTICS OF THREE MODELS HAVING 
45° SWEPTBACK WINGS OF ASPECT RATIO 4. 
Kenneth W. Goodson and Albert G. Few, Jr. 
January 1953. 31p. diagrs., photos., tab. 
(NACA RM L52K21) 



A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF BODY INDENTATION, AS SPEC- 
IFIED BY THE TRANSONIC DRAG-RISE RULE, ON 
THE AERODYNAMIC CHARACTERISTICS AND 
FLOW PHENOMENA OF AN UNSWEPT-WTNG-BODY 
COMBINATION. Claude V. Williams. January 
1953. 38p. diagrs., photos., tabs. 
(NACA RM L52L23) 



TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF ASPECT RATIO, SPANWISE 
VARIATIONS IN SECTION THICKNESS RATIO, AND 
A BODY INDENTATION ON THE AERODYNAMIC 
CHARACTERISTICS OF A 45° SWEPTBACK WING- 
BODY COMBINATION. MelvinM. Carm* 1 
January 1953. 44p. diagrs., tab. 
(NACA RM L52L26b) 



A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF BODY INDENTATION, AS SPEC- 
IFIED BY THE TRANSONIC DRAG -RISE RULE, ON 
THE AERODYNAMIC CHARACTERISTICS AND 
FLOW PHENOMENA OF A 45° SWEPTBACK- WING - 
BODY COMBINATION. Harold L. Robinson. 
February 1953. 33p. diagrs., photos., tab. 
(NACA RM L52L12) 



LIFT, DRAG, AND PITCHING MOMENT OF LOW- 
ASPECT-RATIO WINGS AT SUBSONIC AND SUPER- 
SONIC SPEEDS. Charles F. Hall. April 1953. 
132n ; diagrs., tabs. (NACA RM A53A30) 



WIND-TUNNEL INVESTIGATION OF THE VORTEX 
WAKE AND DOWNWASH FIELD BEHIND TRIANGU- 
LAR WINGS AND WING-BODY COMBINATIONS AT 
SUPERSONIC SPEEDS. J. Richard Spahr and 
Robert R. Dickey. June 1953. 92p. diagrs., 
photos., tabs. (NACA RM A53D10) 



THE EFFECT OF NACELLE COMBINATIONS AND 
SIZE ON THE ZERO-UFT DRAG OF A 45° SWEPT- 
BACK WING AND BODY CONFIGURATION AS DE- 
TERMINED BY FREE-FLIGHT TESTS AT MACH 
NUMBERS BETWEEN 0.8 AND 1.3. Sherwood 
Hoffman and William B. Pepper, Jr. June 1953. 
22p. diagrs., photos., tabs. (NACA RM L53E25) 



THE INFLUENCE OF A CHANGE IN BODY SHAPE 
ON THE EFFECTS OF TWIST AND CAMBER AS 
DETERMINED BY A TRANSONIC WIND-TUNNEL 
INVESTIGATION OF A 45° SWEPTBACK WING- 
FUSELAGE CONFIGURATION. Daniel E. Harrison. 
August 1953. 23p. diagrs., tab. 
(NACA RM L53B03) 



A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF BODY INDENTATION ON THE 
AERODYNAMIC CHARACTERISTICS OF AN 
APPROXIMATE-DELTA-WING-BODY CONFIGURA- 
TION, AND A COMPARISON WITH A WING OF 
REVERSED PLAN FORM. Claude V. Williams. 
August 1953. 36p. diagrs., photos., tabs. 
(NACA RM L53F05a) 



A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECT OF MODIFICATIONS TO AN IN- 
DENTED BODY IN COMBINATION WITH A 45° 
SWEPTBACK WING. Donald L. Loving. September 
1953. 29p. diagrs., photos., tabs. 
(NACA RM L53F02) 



INVESTIGATION OF SPOILER AILERONS WITH AND 
WITHOUT A GAP BEHIND THE SPOILER ON A 45° 
SWEPTBACK WING-FUSELAGE COMBINATION AT 
MACH NUMBERS FROM 0.60 TO 1.03. F. E. West, 
Jr., William Solomon, and Edward M. Brummal. 
September 1953. 38p. diagrs. (NACA RM L53G07a) 



TRANSONIC FLIGHT TESTS TO DETERMINE ZERO- 
UFT DRAG AND PRESSURE RECOVERY OF NA- 
CELLES LOCATED AT THE WING ROOT ON A 45° 
SWEPTBACK WING AND BODY CONFIGURATION. 
Sherwood Hoffman and Austin L. Wolff. September 
1953. 31p. diagrs., photos., tabs. 
(NACA RM L53H20) 



THEORETICAL CALCULATIONS OF THE STABILI- 
TY DERIVATIVES AT SUPERSONIC SPEEDS FOR A 
HIGH-SPEED AIRPLANE CONFIGURATION. 
Kenneth Margolis and Percy J. Bobbitt. October 
1953. 59p. diagrs., tab. (NACA RM L53G17) 



(1) AERODYNAMICS 



109 



RELATIONSHIP OF FLOW OVER A 45° SWEPT - 
BACK WING WITH AND WITHOUT LEADING-EDGE 
CHORD-EXTENSIONS TO LONGITUDINAL STABIL- 
ITY CHARACTERISTICS AT MACH NUMBERS FROM 
60 TO 1.03. F. E. West. Jr . and James H. : 
Henderson. October 1953. 47p. diagrs., photos. 
(NACARM L53H18b) 



DEVELOPMENT OF A SUPERSONIC AREA RULE 
AND AN APPLICATION TO THE DESIGN OF A 
WING-BODY COMBINATION HAVING HIGH LIFT- 
TO-DRAG RATIOS. Richard T. Whitcomb and 
Thomas L. Fischetti. October 1953. 21p. diagrs., 
tabH. (NACA RM L53H31a) 



THE EFFECT OF NOSE RADIUS AND SHAPE ON 
THE AERODYNAMIC CHARACTERISTICS OF A 
FUSELAGE AND A WING-FUSELAGE COMBINATION 
AT ANGLES OF ATTACK. John P. Gapcynski and 
A. Warner Robins. October 1953. 23p. diagrs. 
(NACA RM L53I23a) 



FLIGHT MEASUREMENTS OF THE HORIZONTAL- 
TAIL LOADS ON A SWEPT -WING FIGHTER AIR- 
PLANE AT TRANSONIC SPEEDS. Melvln Sadoff. 
November 1053. 58p. diagrs., photo., Ub. 
(NACA RM A53G10) 



AN INVESTIGATION OF THE TRANSONIC AREA 
RULE BY FLIGHT TESTS OF A SWEPTBACK WING 
ON A CYLINDRICAL BODY WITH AND WITHOUT 
BODY INDENTATION BETWEEN MACH NUMBERS 
0.9 AND i.6. Sherwood Hoiiman. December 1953. 
24p. diagrs., photos., tabs. (NACARM L53J20a) 



FLIGHT INVESTIGATION OF ENGINE NACELLES 
AND WING VERTICAL POSITION ON THE DRAG OF 
A DELTA-WING AIRPLANE CONFIGURATION 
FROM MACH NUMBER 0.8 TO 2.0. Joseph H. Judd. 
March 1954. 39p. diagrs., photos., tabs. 
(NACA RM L53L2^ 



TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF BODY INDENTATION FOR 
BOATTAIL AND CYLINDRICAL AFTERBODY 
SHAPES ON THE AERODYNAMIC CHARACTERIS- 
TICS OF AN UNSWEPT-WING-BODY COMBINA- 
TION. Thomas C. Kelly. March 1954. 22p. 
diagrs., tab. (NACA RM L54A08) 



TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF TAPER RATIO, BODY INDEN- 
TATION, FKED TRANSITION, AND AFTERBODY 
SHAPE ON THE AERODYNAMIC CHARACTERIS- 
TICS OF A 45° SWEPTBACK WING-BODY COMBI- 
NATION. Francis G. Morgan, Jr., and Melvin M. 
Carmel. March 1954. 37p. diagrs., tab. 
(NACA RM L54A15) 



THE EFFECT OF NACELLE LOCATION ON THE 
ZERO-LIFT DRAGS OF 45° SWEPTBACK WING- 
BODY CONFIGURATIONS HAVING BOATTAIL AND 
CYLINDRICAL AFTERBODIES AS DETERMINED BY 
FLIGHT TESTS AT TRANSONIC SPEEDS. Sherwood 
Hoffman and Austin L. Wolff. March 1954. 29p. 
diagrs., photos., tabs. (NACA RM L54B02) 



THE EFFECT OF A CHANGE IN BODY SHAPE ON 
THE LOADING OF A 45° SWEPTBACK WING-BODY 
COMBINATION AT TRANSONIC SPEEDS. Donald L. 
Loving. April 1954. 67p. diagrs., photo. 
(NACA RM L54B09) 



EFFECTS OF SPOILER AILERONS ON THE AERO- 
DYNAMIC LOAD DISTRIBUTION OVER A 45° 
SWEPTBACK WING AT MACH NUMBERS FROM 0,60 
TO 1.03. Joseph M. Hallissy, Jr., F. E. West, Jr., 
and George Liner. May 1954. 162p. diagrs., tabs. 
(NACA RM L54C17a) 



LOW- AMPLITUDE DAMPING-IN-PITCH CHARAC- 
TERISTICS OF TAILLESS DELTA-WTNG-BOBY 
COMBINATIONS AT MACH NUMBERS FROM 0.80 
TO 1.35 AS OBTAINED WITH ROCKET -POWERED 
MODELS. Charles T. D'Alutolo. June 1954. 34p. 
diagrs., photos., tab. (NACA RM L54D29) 



THE EFFECT OF CANOPY LOCATION ON THE 
AERODYNAMIC CHARACTERISTICS OF A SWEPT- 
BACK WING-BODY CONFIGURATION AT TRAN- 
SONIC SPEEDS. Harold L. Robinson. June 1954. 
14p. diagrs., photo. (NACA RM L54E11) 



A FLIGHT INVESTIGATION AT TRANSONIC SPEEDS 
OF THE AERODYNAMIC CHARACTERISTICS OF A 
MODEL HAVING A THIN UNSWEPT WING OF 
ASPECT RATIO 3.1. Maurice D. White. August 
1954. 41p. diagrs., photo., tabs. 
(NACA RM A54E12) 



AN EXPERIMENTAL INVESTIGATION OF REDUC- 
TION IN TRANSONIC DRAG RISE AT ZERO LIFT BY 
THE ADDITION OF VOLUME TO THE FUSELAGE 
OF A WING-BODY-TAIL CONFIGURATION AND A 
COMPARISON WITH THEORY. George H. Holdaway 
August 1954. 35p. diagrs., photos., tabs. 
(NACA RM A54F22) 



INVESTIGATION OF THE EFFECT OF INDENTATION 
ON AN M -PLAN -FORM- WING- BODY COMBINATION 
AT TRANSONIC SPEEDS. Donald L. Loving. 
August 1954. 24p. diagrs., photos., tab. 
(NACA RM L54F14) 



AN INVESTIGATION OF THE EFFECTS OF A GEO- 
METRIC TWIST ON THE AERODYNAMIC LOADING 
CHARACTERISTICS OF A 45° SWEPTBACK WING- 
BODY CONFIGURATION AT TRANSONIC SPEEDS. 
Claude V. Williams. October 1954. 87p. diagrs., 
photos., tabs. (NACA RM L54H18) 



A FLIGHT INVESTIGATION OF THE TRANSONIC 
AREA RULE FOR A 52.5° SWEPTBACK WING-BODY 
CONFIGURATION AT MACH NUMBERS BETWEEN 
0.8 AND 1.6. Sherwood Hoffman. November 1954. 
25p. diagrs., photos., tab. (NACA RM L54H13a) 



LOW-AMPLITUDE DAMPING-IN-PITCH CHARAC- 
TERISTICS OF FOUR TAILLESS SWEPT WING- 
BODY COMBINATIONS AT MACH NUMBERS FROM 
0.85 TO 1.30 AS OBTAINED WITH ROCKET- 
POWERED MODELS. Charles T. D'Alutolo. 
November 1954. 34p. diagrs., photos., tab. 
(NACA RM L54I10) 



EFFECT OF TAPER RATIO ON LIFT f DRAG, AND 
PITCHING-MOMENT CHARACTERISTICS OF THIN 
WINGS OF ASPECT RATIO 3 WITH 53.10 SWEEP- 
BACK OF LEADING EDGE AT SUBSONIC AND 
SUPERSONIC SPEEDS. Benton E. Wetiel. 
January 1955. 25 p. diagrs., photo., tabs. 
(NACA RM A54 J20) 



LONGITUDINAL STABILITY CHARACTERISTICS 
AT MACH NUMBERS UP TO 0.92 OF A WING- 
BODY-TAIL COMBINATION HAVING A WING WITH 
45° OF SWEEPBACK AND A TAIL IN VARIOUS 
VERTICAL POSITIONS. Jack D. Stephenson, 
Angelo Bandettlni, and Ralph Selan. January 1955. 
64p. diagrs., photos., tabs. (NACA RM A54K09) 



EFFECTS OF BODY INDENTATION ON THE DRAG 
CHARACTERISTICS OF A DELTA-WING-BODY, 
COMBINATION AT TRANSONIC SPEEDS . Dewey E . 
Wornom and Robert S. Osborne. January 1955. 
32p. diagrs., photos., tabs. (NACA RM L54K12a) 



110 



< 1 ) AERODYNAMICS 



EFFECTS OF INCREASING REYNOLDS NUMBER 
FROM 2 x 106 TO 6 x 106 ON THE AERODYNAMIC 
CHARACTERISTICS AT TRANSONIC SPEEDS OF A 
450 SWEPT WING WITH 60 LEADING- EDGE DROOP 
James W. Schmeer and J. Lawrence Cooper. 
February 1955. 22p. diagrs., photo. 
(NACA RM L54L10) 



THE LONGITUDINAL CHARACTERISTICS AT MACH 
NUMBERS UP TO 0.92 OF SEVERAL WING- 
FUSELAGE-TAIL COMBINATIONS HAVING SWEPT - 
BACK WINGS WITH NACA FOUR-DIGIT THICKNESS 
DISTRIBUTIONS . F re d B . Sutton and Je raid K . 
Dickson. March 1955. 128p. diagrs., photos., tab. 



THE ROLLING MOMENT DUE TO SIDESLIP OF 
SWEPT WINGS AT SUBSONIC AND TRANSONIC 
SPEEDS. Edward C . Polhamus and William C . 
S lee man, Jr. March 1955. 81p. diagrs., photos., 
tabs. (NACA RM L54L01) 



AN EXPERIMENTAL INVESTIGATION OF TWO 
METHODS FOR REDUCING TRANSONIC DRAG OF 
SWEPT-WING AND BODY COMBINATIONS. John B. 
McDevltt. April 1955. 27p. diagrs., photos. 
(NACA*RM A55B21) 



EXPLORATORY INVESTIGATION OF THE LOW- 
SPEED STATIC STABILITY OF A CONFIGURATION 
EMPLOYING THREE IDENTICAL TRIANGULAR 
WING PANELS AND A BODY OF EQUAL LENGTH. 
Noel K. Delany. April 1955. 25p. diagrs., photos. 
(NACA RM A55C28) 



A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE LONGITUDINAL FORCE AND MOMENT CHAR- 
ACTERISTICS OF TWO DELTA WINGS AND ONE 
CLIPPED-TIP DELTA WING OF 4 PERCENT 
THICKNESS ON A SLENDER BODY. William E. 
Palmer and Dale L. Burrows. April 1955. 31p. 
diagrs., photo. (NACA RM L55A07a) 



FLUTTER EXPERIENCES WITH THIN POINTED-TTP 
WINGS DURING FLIGHT TESTS OF ROCKET- 
PROPELLED MODELS AT MACH NUMBERS FROM 
0.8 TO 1.95. Harvey A. Wallskog. April 1955. 
-32p. diagrs., photos., tabs, (NACA RM L55A14) 



LIFT, DRAG, AND LONGITUDINAL STABILITY AT 
MACH NUMBERS FROM 0.8 TO 2.1 OF A ROCKET- 
POWERED MODEL HAVING A TAPERED UNSWEPT 
WING OF ASPECT RATIO 3 AND INLINE TAIL 
SURFACES. Warren Gillespie, Jr. April 1955. 
29p. diagrs., photo., tabs. (NACA RM L55B10) 



COMPARISON OF THE STATIC STABILITY OF A 
68.7° DELTA-WING MODEL WITH DIHEDRAL AND 
A TWISTED AND CAMBERED WING MODEL OF THE 
SAME PLAN FORM. John W. Paulson. April 1955. 
18p. diagrs., tab. (NACA RM L55B11) 



INVESTIGATION OF INTERFERENCE LIFT, DRAG, 
AND PITCHING MOMENT OF A SERIES OF TRI- 
ANGULAR WING AND BODY COMBINATIONS AT A 
MACH NUMBER OF 1.62. Donald E. Coletti. May 
1955. 49p. diagrs., photo., tabs. 
(NACA RM L55B25) 



INVESTIGATION OF THE EFFECTS OF AN AIRFOIL 
SECTION MODIFICATION ON THE AERODYNAMIC 
CHARACTERISTICS AT SUBSONIC AND SUPERSONIC 
SPEEDS OF A THIN SWEPT WING OF ASPECT 
RATIO 3 IN COMBINATION WITH A BODY. David 
Graham and William T. Evans. June 1955. 46p. 
diagrs., tabs. (NACA RM A55D11) 



INVESTIGATION OF THE EFFECTS OF BODY 
INDENTATION AND OF WING -PL AN -FORM 
MODIFICATION ON THE LONGITUDINAL CHARAC- 
TERISTICS OF A 60° SWEPT -WING-BODY COMBI- 
NATION AT MACH NUMBERS OF 1.41, 1.61, AND 
2.01. John R. Sevier, Jr. July 1955. 37p. diagrs., 
tab. (NACA RM L55E17) 



AN EXPERIMENTAL INVESTIGATION AT A MACH 
NUMBER OF 2.01 OF THE EFFECTS OF BODY 
CROSS-SECTION SHAPE ON THE AERODYNAMIC 
CHARACTERISTICS OF BODIES AND WING-BODY 
COMBINATIONS. Harry W. Carlson and John P. 
Gapcvnski. Julv 1955. 29o. diagr«.. t»h« ; 
(NACA RM L55E23) 



ADDITIONAL COMPARISONS BETWEEN COMPUTED 
AND MEASURED TRANSONIC DRAG-RISE COEFFI- 
CIENTS AT ZERO LIFT FOR WING-BODY-TAIL 
CONFIGURATIONS. George H. Holdaway. August 
1955. 43p. diagrs., photo., tabs. 
(NACA RM A55F06) 



SUMMARY AND ANALYSIS OF HORIZONTAL-TAIL 
CONTRIBUTION TO LONGITUDINAL STABILITY OF 
SWEPT-WING AIRPLANES AT LOW SPEEDS. 
Robert H. Neely and Roland F. Griner. August 1955. 
ii, 133p. diagrs., tabs. (NACA RM L55E23a) 



A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE STATIC LONGITUDINAL CHARACTERISTICS 
OF A 3-PERCENT-THICK, ASPECT-RATIO-3, 
DELTA WING CAMBERED AND TWISTED FOR HIGH 
LIFT -DRAG RATIOS. Dale L. Burrows and Warren 
A. Tucker. August 1955. 38p. diagrs., photos., 
tab. (NACA RM L55F02a) 



A FREE-FLIGHT INVESTIGATION OF THE DRAG 
COEFFICUiNTS OF TWO SINGLE-ENGINE SUPER- 
SONIC INTERCEPTOR CONFIGURATIONS FROM 
MACH NUMBER 0.8 TO 1.90 TO DETERMINE THE 
EFFECT OF INLET AND ENGINE LOCATION. 
APPENDDC: SEPARATION CHARACTERISTICS OF 
A MODEL FROM A LARGE UNDERSLUNG BOOSTER 
AT MACH NUMBER 1.95. Joseph H. Judd. 
September 1955. 49p. diagrs., photos., tabs. 
(NACA RM L55G05a) 



EFFECT OF LEADING-EDGE SWEEPBACK ON LIFT, 
DRAG, AND PITCHING -MOMENT CHARACTERIS- 
TICS OF THIN WINGS OF ASPECT RATIO 3 AND 
TAPER RATIO 0.4 AT SUBSONIC AND SUPERSONIC 
SPEEDS. Benton E. Wetzel. November 1955. 22p. 
diagrs., tabs. (NACA RM A55H04a) 



THE EFFECT OF LEADING-EDGE DROOP UPON 
THE PRESSURE DISTRIBUTION AND AERODYNAM- 
IC LOADING CHARACTERISTICS OF A 45° SWEPT- 
BACK WING AT TRANSONIC SPEEDS. James W. 
Schmeer. November 1955. 42p. diagrs., photos. 
(NACA RM L55H8) 



INVESTIGATION OF INTERFERENCE LIFT, DRAG, 
AND PITCHING MOMENT OF A SERIES OF 
TRIANGULAR-WING AND BODY COMBINATIONS 
AT A MACH NUMBER OF 1.94. Donald E. Coletti. 
December 1955. 52p. diagrs., photo., tabs. 
(NACA RM L55I14) 



THE EFFECT OF LEADING-EDGE EXTENSIONS 
OF THE LONGITUDINAL CHARACTERISTICS AT 
MACH NUMBERS UP TO 0.92 OF A WING- 
FUSELAGE-TAIL COMBINATION HAVING A 40° 
SWEPTBACK WING WITH NACA 64A THICKNESS 
DISTRIBUTION. Fred B. Sutton. January 1956. 
52p. diagrs., photos., tabs. (NACA RM A55I29) 



Ill 



(1) AERODYNAMICS 



EXPERIMENTAL STUDY .OF A METHOD OF DE- 
SIGNING THE SWEPTBACK-WING-FUSELAGE 
JUNCTURE TO REDUCE THE DRAG AT MODERATE 
SUPERSONIC SPEEDS. Robert R. Howell. January 
1956. 20p. diagrs., photos., tabs. 
(NACA RM L55H05a) 



INFLUENCE OF THE BODY FLOW FIELD ON THE 
ZERO-LIFT WAVE DRAG OF WING-BODY COMBI- 
NATIONS MODIFIED IN ACCORDANCE WITH THE 
TRANSONIC AREA RULE. William A. Page. 
February 1958. 26p. diagrs. (NACA RM A55K10) 



FLIGHT MEASUREMENTS OF HORIZONTAL -TAIL 
LOADS ON THE DOUGLAS X-3 RESEARCH AIR- 
PLANE. Harriet J. Stephenson. April 1956. 33p. 
diagrs., photo., tab. (NACA RM H56A23) 



LOW -SPEED INVESTIGATION OF THE EFFECTS 
OF WING DIHEDRAL ANGLE AND FIN LENGTH ON 
THE STATIC STABILITY CHARACTERISTICS OF A 
MODEL HAVING AN 82° DELTA WING. Kenneth P. 
Spreemann. April 1956. 30p. diagrs. 
(NACA RM L55L30a) 



DATA FROM LARGE-SCALE LOW-SPEED TESTS 
OF AIRPLANE CONFIGURATIONS WITH A THIN 45° 
SWEPT WING INCORPORATING SEVERAL 
LEADING-EDGE CONTOUR MODIFICATIONS. 
William T. Evans. May 1956. llOp. diagrs., 
photo., tabs. (NACA RM A56B17) 



EFFECT OF AIRPLANE CONFIGURATION ON 
STATIC STABILITY AT SUBSONIC AND TRANSONIC 
SPEEDS. Edward C. Polhamus and Joseph M. 
Hallissy, Jr. May 1956. 17p. diagrs. 
(NACA RM L56A09a) 



EFFECT OF WING CAMBER AND TWIST AT MACH 
NUMBERS FROM 1.4 TO 2.1 ON THE LIFT, DRAG, 
AND LONGITUDINAL STABILITY OF A ROCKET- 
POWERED MODEL HAVING A 52.5° SWEPTBACK 
WING OF ASPECT RATIO 3 AND INLINE TAIL SUR- 
FACES. Warren Gillespie, Jr. May 1958. 29p. 
diagrs., photos., tabs. (NACA RM L58C16) 



EFFECT OF WING SIZE AND AMOUNT OF INDEN- 
TATION ON APPLICABILITY OF TRANSONIC AREA 
RULE TO SWEPT- WING CONFIGURATIONS. 
James Rudyard Hall. July 1956. 33p. diagrs., 
photos., tabs. (NACA RM L55F03) 



TRANSONIC WIND-TUNNEL INVESTIGATION OF 
STATIC LONGITUDINAL FORCE AND MOMENT ' 
CHARACTERISTICS OF TWO WING-BODY COMBI- 
NATIONS WITH CLIPPED-TIP AND FULL DELTA 
WINGS OF ASPECT RATIO 1.73. Dale L. Burrows. 
September 1956. 26p. diagrs. (NACA RM L56F21) 



EFFECT OF A FUSELAGE ON THE LOW-SPEED 
LONGITUDINAL AERODYNAMIC CHARACTERISTICS 
OF A 45° SWEPTBACK WING WITH DOUBLE 
SLOTTED FLAPS. Rodger L. Naeseth. September 
1956. 31 p. diagrs., tabs. (NACA RM L56G02) 



COMBINED EFFECTS OF WING TAPER RATIO AND 
LOW HORIZONTAL -TAIL POSITION ON LONGITU- 
DINAL STABILITY OF A 45° SWEPTBACK WING- 
BODY COMBINATION AT TRANSONIC SPEEDS. 
Stanley H. Spooner. October 1956. 28p. diagrs., 
tab. (NACA RM L56H24) 



SOME CONSIDERATIONS OF THE INFLUENCE OF 
BODY CROSS-SECTIONAL SHAPE ON THE LIFTING 
EFFICIENCY OF WING-BODY COMBINATIONS AT 
SUPERSONIC SPEEDS. E. B. Klunker and Keith C. 
Harder. October 1956. 20p. diagrs. 
(NACA RM L56H30) 



LIFT AND CENTER OF PRESSURE OF WING-BODY- 
TAIL COMBINATIONS AT SUBSONIC, TRANSONIC, 
AND SUPERSONIC SPEEDS. William C. Pitts, Jack 
N. Nielsen, and George E. Kaattari. 1957. ii, 70p. 
diagrB., tabs. (NACA Rept. 1307) 



ON SLENDER-BODY THEORY AT TRANSONIC 
SPEEDS. Keith C. Harder and E. B. Klunker. 
1957. ii, 6p. (NACA Rept. 1315. Supersedes 
TN 3815) 



MINIMUM WAVE DRAG FOR ARBITRARY ARRANGE- 
MENTS OF WINGS AND BODIES. Robert T. Jones. 
1957. ii, 6p. diagrs., photo. (NACA Rept. 1335. 
Supersedes TN 3530) 



FLIGHT INVESTIGATION AND THEORETICAL CAL- 
CULATIONS OF THE FUSELAGE DEFORMATIONS 
OF A SWEPT -WING BOMBER DURING PUSH-PULL 
MANEUVERS. Alton P. Mayo. March 1957. 51p. 
diagrs., photo., tabs. (NACA RM L56L05) 



GROUND EFFECTS ON THE LONGITUDINAL CHAR- 
ACTERISTICS OF TWO MODELS WITH WINGS 
HAVING LOW ASPECT RATIO AND POINTED TD?S. 
Donald A. Buell and Bruce E. Tin ling. July 1957. 
48p. diagrs., photos., tabs. (NACA TN 4044. 
Supersedes RM A55E04) 



ELLD7TIC CONES ALONE AND WITH WINGS AT 
SUPERSONIC SPEEDS. Leland H. Jorgeneen. 
October 1957. 55p. diagrs., photos. 
(NACA TN 4045) 



WIND-TUNNEL INVESTIGATION OF THE STATIC 
LATERAL STABILITY CHARACTERISTICS OF 
WING-FUSELAGE COMBINATIONS AT HIGH SUB- 
SONIC SPEEDS. TAPER-RATIO SERIES. James 
W. Wiggins and Paul G. Fournier. October 1957. 
25p. diagrs., photos. (NACA TN 4174. Supersedes 
RM L53B25a) 



CONTRIBUTION OF THE WING PANELS TO THE 
FORCES AND MOMENTS OF SUPERSONIC WING- 
BODY COMBINATIONS AT COMBINED ANGLES. 
J. Richard Spahr. January 1958. 62p. diagrs., 
photo., tabs. (NACA TN 4146) 



WIND-TUNNEL INVESTIGATION OF EFFECT OF 
SWEEP ON ROLLING DERIVATIVES AT ANGLES OF 
ATTACK UP TO 13° AND AT HIGH SUBSONIC MACH 
NUMBERS, INCLUDING A SEMIEMPIRICAL 
METHOD OF ESTIMATING THE ROLLING DERIVA- 
TIVES. James W. Wiggins. January 1958. 47p. 
diagrs., tab. (NACA TN 4185. Supersedes 
RM L54C26) 

A NUMERICAL METHOD FOR EVALUATING WAVE 
DRAG. Maurice S. Cahn and Walter B. Ols tad, 
June 1958. 13p. diagrs., tabs. (NACA TN 4258) 



A FUSELAGE ADDITION TO INCREASE DRAG-RISE 
MACH NUMBER OF SUBSONIC AIRPLANES AT 
LIFTING CONDITIONS. Richard T. Whitcomb. 
June 1958. 38p. diagrs., photos., tab. 
(NACA TN 4290) 



A BODY MODIFICATION TO REDUCE DRAG DUE 
TO WEDGE ANGLE OF WING WITH UNSWEPT 
TRAILING EDGE. Wtlliara C. Pitts and Jack N. 
Nielsen. July 1958. I3p. (NACA TN 4277) 



WIND-TUNNEL INVESTIGATION OF THE HIGH- 
SUBSONIC STATIC LONGITUDINAL STABILITY 
CHARACTERISTICS OF SEVERAL WING-BODY CON- 
FIGURATIONS DESIGNED FOR HIGH LIFT -DRAG 
RATIOS AT A MACH NUMBER OF 1.4. Paul G. 
Fournier. July 1958. 42p. diagrs., photo., tab. 
(NACA TN 4340) 



112 



(1) AERODYNAMICS 



IDEALIZED WINGS AND WING-BODIES AT A MACH 
NUMBER OF 3. Elliott D. Katz en. July 1958. lip. 

diagrs. {NACA TN 4361) 



SOME FACTORS AFFECTING THE VARIATION OF 
PITCHING MOMENT WITH SIDESLIP OF AIRCRAFT 
CONFIGURATIONS. Edward C. Polhamus. August 
1958. 35p. diagrs., photo. (NACA TN 4016. 
Supersedes RM L55E20b) 



INVESTIGATION OF MINIMUM DRAG AND MAXI- 
MUM LIFT-DRAG RATIOS OF SEVERAL WING-BODY 
COMBINATIONS INCT.imTNG A CAMBERED TRI- 
ANGULAR WING AT LOW REYNOLDS NUMBERS 
AND AT SUPERSONIC SPEEDS. Clinton E. Brown 
and L. K. Har grave. September 1958. 62p. diagrs., 
photos., tabs. (NACA TN 4020. Supersedes 
RM L51E11) 



(1.7. 1.1.2) 
Wing-Nacelle 



AERODYNAMIC CHARACTERISTICS AT SUPER- 
SONIC SPEEDS OF A SERIES OF WING-BODY 
COMBINATIONS HAVING CAMBERED WINGS WITH 
AN ASPECT RATIO OF 3.5 AND A TAPER RATIO 
OF 0.2. EFFECT AT M = 1.60 OF NACELLE 
SHAPE AND POSITION ON THE AERODYNAMIC 
CHARACTERISTICS IN PITCH OF TWO WING-BODY 
COMBINATIONS WITH 47° SWEPT BACK WINGS. 
Lowell E. Hasel and John R. Sevier, Jr. January 
1952. 31p. diagrs., photos., tabs. 
(NACA RM L51K14a) 



AERODYNAMIC CHARACTERISTICS AT SUPER- 
SONIC SPEEDS OF A SERIES OF WING-BODY 
COMBINATIONS HAVING CAMBERED WINGS WITH 
AN ASPECT RATIO OF 3.5 AND A TAPER RATIO OF 
0.2. EFFECTS OF SWEEP ANGLE AND THICKNESS 
RATIO ON THE STATIC LATERAL STABILITY 
CHARACTERISTICS AT M = 1.60. M. Leroy 
Spearman and John H. Hilton, Jr. January 1952. 
31p. diagrs., tabs. (NACA RM L51K15a) 



AERODYNAMIC CHARACTERISTICS AT SUPER- 
SONIC SPEEDS OF A SERIES OF WING-BODY COM- 
BINATIONS HAVING CAMBERED WiNGS WITH AN 
ASPECT RATIO OF 3.5 AND A TAPER RATIO OF 
0.2. EFFECT AT M = 2.01 OF NACELLE SHAPE 
AND POSITION ON THE AERODYNAMIC CHARAC- 
TERISTICS IN PITCH OF TWO WING-BODY COM- 
BINATIONS WITH 47° SWT.J'TBACK WINGS. 
Cornelius Driver. July 1!<52. 27p. diagrs., photos., 
tab. (NACARML52F0'-; 



AERODYNAMIC CHARACTERISTICS AT SUPER- 
SONIC SPEEDS OF A SERIES OF WING-BODY COM- 
BINATIONS HAVING CAMBERED WINGS WITH AN 
ASPECT RATIO OF 3.5 AND A TAPER RATIO OF 
0.2. EFFECTS OF SWEEP ANGLE AND THICKNESS 
RATIO ON THE STATIC LATERAL STABILITY 
CHARACTERISTICS AT M = 2.01. Clyde V. 
Hamilton. August 1952. 37p. diagrs., tabs. 
(NACA RM L52E23) 



EFFECTS OF SYSTEMATICALLY VARYING THE 
SPANW1SE AND VERTICAL LOCATION OF AN EX- 
TERNAL STORE ON THE AERODYNAMIC CHARAC- 
TERISTICS OF AN UNSWEPT TAPERED WING OF 
ASPECT RATIO 4 AT MACH NUMBERS OF 1.41, 
1.62, AND 1.96. Carl R. Jacobsen. August 1952. 
34p. diagrs. (NACA RM L52F13) 



A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF NACELLE SHAPE AND POSITION 
ON THE AERODYNAMIC CHARACTERISTICS OF 
TWO 47° SWEPTBACK WING-BODY CONFIGURA- 
TIONS. Ralph P. Bielat and Daniel E. Harrison. 
September 1952. 87p. diagrs., photos., tab. 
(NACA RM L52G02} 



INVESTIGATION AT HIGH SUBSONIC SPEEDS OF 
BODIES MOUNTED FROM THE WING OF AN 
UNSWEPT-WING -FUSELAGE MODEL, INCLUDING 
MEASUREMENTS OF BODY LOADS. H. Norman 
Silvers and Thomas J. King, Jr. November 1952. 
37p. dia*rs., photos., tabs, (NACA RM L52J08) 



EFFECTS OF THE SPANWISE, CHORDWISE, AND 
VERTICAL LOCATION OF AN EXTERNAL STORE 
ON THE AERODYNAMIC CHARACTERISTICS OF A 
45° SWEPTBACK TAPERED WING OF ASPECT 
RATIO 4 AT MACH NUMBERS OF 1.41, 1.62, AND 
196. Carl R. Jacobsen. January 1953. 31p. 
diagrs., photo, (NACA KM L52J27) 



EFFECTS OF SIZE OF EXTERNAL STORES ON THE 
AERODYNAMIC CHARACTERISTICS OF AN UN- 
SWEPT AND A 45° SWEPTBACK WING OF ASPECT 
RATIO 4 AND A 60° DELTA WING AT MACH NUM- 
BERS OF 1.41, 1.62, AND 1.96. CarlR. Jacobsen. 
January 1953. 55p. diagrs., photos., tab. 
(NACA RM L52K20a) 



THE EFFECT OF NACELLE COMBINATIONS AND 
SIZE ON THE ZERO-UFT DRAG OF A 45° SWEPT- 
BACK WING AND BODY CONFIGURATION AS DE- 
TERMINED BY FREE -FLIGHT TESTS AT MACH 
NUMBERS BETWEEN 0.8 AND 1.3. Sherwood 
Hoffman and William B. Pepper, Jr. June 1953. 
22p. diagrs., photos., tabs. (NACARM L53E25) 



TRANSONIC FLIGHT TESTS TO DETERMINE ZERO- 
LIFT DRAG AND PRESSURE RECOVERY OF NA- 
CELLES LOCATED AT THE WING ROOT ON A 45° 
SWEPTBACK WING AND BODY CONFIGURATION. 
Sherwood Hoffman and Austin L. Wolff. September 
1953. 31p. diagrs., photos., tabs. 
(NACA RM L53H20) 



FLIGHT INVESTIGATION OF ENGINE NACELLES 
AND WING VERTICAL POSITION ON THE DRAG OF 
A DELTA-WING AIRPLANE CONFIGURATION 
FROM MACH NUMBER 0.8 TO 2.0. Joseph H. Judd. 
March 1954. 39p. diagrs., photos., tabs. 
(NACA RM L53L21) 



WIND-TUNNEL INVESTIGATION AT HIGH SUBSONIC 
SPEEDS OF THE EFFECTS OF WING-MOUNTED 
EXTERNAL STORES ON THE LOADING AND AERO- 
DYNAMIC CHARACTERISTICS IN PITCH OF A 45° 
SWEPTBACK WING COMBINED WITH A FUSELAGE . 
H. Norman Silvers, Thomas J. King, Jr., and 
WiUiamJ. Alford, Jr. March 1954. 36p. diagrs., 
tabs. (NACA RM L54A21) 



THE EFFECT OF NACELLE LOCATION ON THE 
ZERO- LIFT DRAGS OF 45° SWEPTBACK WING- 
BODY CONFIGURATIONS HAVING BOATTAIL AND 
CYLINDRICAL AFTERBODIES AS DETERMINED BY 
FLIGHT TESTS AT TRANSONIC SPEEDS. Sherwood 
Hoffman and Austin L. Wolff. March 1954. 29p. 
diagrs., photos., tabs. (NACA RM L54B02) 



INVESTIGATION AT HIGH SUBSONIC SPEEDS OF 
FINNED AND UNFINNED BODIES MOUNTED AT 
VARIOUS LOCATIONS FROM THE WINGS OF UN- 
SWEPT, AND SWEPT-WING-FUSELAGE MODELS, 
INCLUDING MEASUREMENTS OF BODY LOADS. 
William J. Alford, Jr., and H. Norman Silvers. 
April 1954. 93p. diagrs., photos., tabs. 
(NACA RM L54B18) 



AERODYNAMIC LOADS ON AN EXTERNAL STORE 
ADJACENT TO A 45° SWEPTBACK WING AT MACH 
NUMBERS FROM 0.70 TO 1.96, INCLUDING AN 
EVALUATION OF TECHNIQUES USED. Lawrence 
D. Guy and William M. Hadaway. November 1955. 
109p. diagrs., photo., tab. (NACA RM L55H12) 



113 



(1) AERODYNAMICS 



INVESTIGATION AT HIGH SUBSONIC SPEEDS OF 
SOME EFFECTS OF SIDESLIP ON THE AERODY- 
NAMIC LOADS ON FINNED AND UNFINNED BODIES 
MOUNTED FROM THE WING OF A SWEPT -WING- 
FUSELAGE MODEL. Thomas J. King, Jr. April 
1956. 50p. diagrs., tabs. (NACA RM L56A24) 



THEORETICAL CALCULATIONS OF SUPERSONIC 
WAVE DRAG AT ZERO LIFT FOR A PARTICULAR 
STORE ARRANGEMENT. Kenneth Margolis, 
Frank S. Malvestuto, Jr., and Peter J, Maxie, Jr. 
January 1958. 37p. diagrs., tab. (NACA TN 4120) 



(1.7.1.1.3) 
Tail-Wing and Fuselage 



LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS OF AN AIRPLANE MODEL HAVING A 
42.8° SWEPTBACK CIRCULAR-ARC WING WITH 
ASPECT RATIO 4.00, TAPER RATIO 0.50, AND 
SWEPTBACK TAIL SURFACES. Joseph Weil, Paul 
Comisarow, and Kenneth W. Goodson. October 17, 
1947. 84p. diagrs., photos., tab. 
(NACA RM L7G28) 



SUPERSONIC-TUNNEL TESTS OF TWO SUPER- 
SONIC AIRPLANE MODEL CONFIGURATIONS. 
Macon C. Ellis, Jr., Loweii E. Hasei, and Carl E. 
Grigsby. December 31, 1947. 49p, diagrs., 
photos., tab. (NACA RM L7J15) 



FLIGHT TESTS AT TRANSONIC AND SUPERSONIC 
SPEEDS OF AN AIRPLANE-LIKE CONFIGURATION 
WITH THIN STRAIGHT SHARP-EDGE WINGS AND 
TAIL SURFACES. Clarence L. Gillis and Jesse L. 
Mitchell. January 5, 1949. 37p. diagrs., photos., 
tab. (NACA RM L8K04a) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR -ARC SECTIONS AND 40° SWEEPBACK. 
STATIC LONGITUDINAL STABILITY AND CONTROL 
CHARACTERISTICS AT A MACH NUMBER OF 1.59. 
M. Leroy Spearman and John H. Hilton, Jr. 
June 29, 1950. 22p. diagrs., photo., tab. 
(NACA RM L50E12) 



PRELIMINARY RESULTS OF THE FLIGHT INVES- 
TIGATION BETWEEN MACH NUMBERS OF 0.80 AND 
1.36 OF A ROCKET -POWERED MODEL OF A 
SUPERSONIC AIRPLANE CONFIGURATION HAVING 
A TAPERED WING WITH CIRCULAR-ARC SECTIONS 
AND 40° SWEEPBACK. Charles T. D'Aiutolo and 
Homer P. Mason. October 31, 1950. 30p. diagrs., 
photos., tab. (NACA RM L 5 OH 29a) 



DETERMINATION OF LONGITUDINAL STABILITY 
OF THE BELL X-l AIRPLANE FROM TRANSIENT 
RESPONSES AT MACH NUMBERS UP TO 1.12 AT 
LIFT COEFFICIENTS OF 0.3 AND 0.6. Ellwyn E. 
Angle and Euclid C. Holleman. November 7, 1950. 
22p diagrs. (NACA RM L 50106a) 



WING-ON AND WING-OFF LONGITUDINAL CHAR- 
ACTERISTICS OF AN AIRPLANE CONFIGURATION 
HAVING A THIN UNSWEPT TAPERED WING OF 
ASPECT RATIO 3, AS OBTAINED FROM ROCKET- 
PROPELLED MODELS AT MACH NUMBERS FROM 
0.8 TO 1.4. Clarence L. Gillis and A. James Vitale. 
March 14, 1951. 52p. diagrs., photos., tabs. 
(NACA RM L50K16) 



ANALYSIS OF LONGITUDINAL STABILITY AND 
TRIM OF THE BELL X-l AIRPLANE AT A LIFT 
COEFFICIENT OF 0.3 TO MACH NUMBERS NEAR 
1.05. Hubert M. Drake, John R. Carden, and 
Harry P. Clagett. October 1951. 30p. diagrs., 
photo., tab. (NACA RM L51H01) 



THE STATIC AND DYNAMIC LONGITUDINAL STA- 
BILITY CHARACTERISTICS OF SOME SUPERSONIC 
AIRCRAFT CONFIGURATIONS. Jesse L. Mitchell. 
January 1952. 19p. diagrs. (NACA RM L52A10a) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR-ARC SECTIONS AND 40° SWEEPBACK. 
ESTIMATED DOWNWASH ANGLES DERIVED FROM 
PRESSURE MEASUREMENTS ON THE TAIL AT 
MACH NUMBERS OF 1.40 AND 1.59. Frederick C. 
Grant and John P. Gapcynski. March 1952. 27p. 
diagrs., photos., tabs. (NACA RM L51L17) 



LONGITUDINAL STABILITY AND DRAG CHARAC- 
TERISTICS AT MACH NUMBERS FROM 0.75 TO 1.5 
OF AN AIRPLANE CONFIGURATION HAVING A 60<> 
SWEPT WING OF ASPECT RATIO 2.24 AS OB- . 
TAINED FROM ROCKET-PROPELLED MODELS. 
A. James Vitale, John C. McFall, Jr., and John D. 
Morrow. April 1952. 43p. diagrs., photos., tabs. 
(NACA RM L51K06) 



LONGITUDINAL AERODYNAMIC CHARACTERISTICS 
OF MODEL AIRPLANE CONFIGURATION EQUIPPED 
WITH A SCALED X-l AIRPLANE WING. James H. 
Parks. April 1952. 37p. diagrs. 
(NACA RM LSlLlOa) 



THE AERODYNAMIC CHARACTERISTICS OF A 
SUPERSONIC AIRCRAFT CONFIGURATION WITH A 
40° SWEPTBACK WING THROUGH A MACH NUM- 
BER RANGE FROM TO 2.4 AS OBTAINED FROM 
VARIOUS SOURCES. M. Leroy Spearman and Ross 
B. Robinson. April 1952. 50p. diagrs., photo., 
tab. (NACA RM L52A21) 



AN INVESTIGATION OF A 0.16-SCALE MODEL OF 
THE DOUGLAS X-3 AIRPLANE. TO DETERMINE 
MEANS OF IMPROVING THE LOW-SPEED LONGI- 
TUDINAL STABILITY AND CONTROL CHARACTER- 
ISTICS. John W. McKee and John M. Riebe. 
November 1952. 90p. diagrs., photos., tabs. 
(NACA RM L52H01) 



LONGITUDINAL STABILITY, CONTROL EFFEC- 
TIVENESS, AND DRAG CHARACTERISTICS AT 
TRANSONIC SPEEDS OF A ROCKET-PROPELLED 
MODEL OF AN AIRPLANE CONFIGURATK)N 
HAVING AN UNSWEPT TAPERED WING OF ASPECT 
RATK) 3.0 AND NACA 65A004.5 AIRFOIL SECTIONS. 
JohnC. McFall, Jr., and James A. Hollinger. 
January 1953. 30p. diagrs., photos. 
(NACA RM L52L04) 



A ROCKET- MODEL INVESTIGATION OF THE LON- 
GITUDINAL STABILITY, LIFT, AND DRAG CHAR- 
ACTERISTICS OF THE DOUGLAS X-3 CONFIGURA- 
TION WITH HORIZONTAL TAIL OF ASPECT RATIO 
4.33. Robert F. Peck and James A. Hollinger. 
August 1953. 33p. diagrs., photos. 
(NACA RM L53F19a) 



COMPARISON OF THEORETICAL AND EXPERI- 
MENTAL ZERO-LIFT DRAG-RISE CHARACTERIS- 
TICS OF WING-BODY-TAIL COMBINATIONS NEAR 
THE SPEED OF SOUND. George H. Holdaway. 
October 1953. 27p. diagrs., tab. 
(NACA RM A53H17) 



114 



(1) AERODYNAMICS 



THEORETICAL CALCULATIONS OF THE STABILI- 
TY DERIVATIVES AT SUPERSONIC SPEEDS FOR A 
HIGH-SPEED AIRPLANE CONFIGURATION. 
Kenneth Margolis and Percy J. Bobbitt. October 
1953. 59p. diagrs., tab. (NACA RM L53G17) 



STATIC LONGITUDINAL STABILITY AND CONTROL 
CHARACTERISTICS OF A l/16-SCALE MODEL OF 
THE DOUGLAS D-558-H RESEARCH AIRPLANE AT 
MACH NUMBERS OF 1.61 AND 2.01. M. Leroy 
Spearman. November 1953. 34p. diagrs., tabs. 
(NACA RM L53I22) 



RECENT DESIGN STUDIES DIRECTED TOWARD 
ELIMINATION OF PITCH-UP. Joseph Weil and 
W. H. Gray. November 1953. 16p. diagrs., tab. 
(NACA RM L53I23c) 



STATIC LATERAL STABILITY CHARACTERISTICS 
OF A 1/16-SCALE MODEL OF THE DOUGLAS 
D-558-U RESEARCH AIRPLANE AT MACH NUM- 
BERS OF 1.61 AND 2.01. Frederick C. Grant and 
Ross B. Robinson. November 1953. 39p. diagrs., 
photo., tabs. (NACA RM L53I29a) 



EFFECTS OF LEADING-EDGE CHORD EXTENSIONS 
AND AN ALL-MOVABLE HORIZONTAL TAIL ON 
THE AERODYNAMIC CHARACTERISTICS OF A 
WING-BODY COMBINATION EMPLOYING A TRI- 
ANGULAR WING OF ASPECT RATIO 3 MOUNTED IN 
A HIGH POSITION AT SUBSONIC AND SUPERSONIC 
SPEEDS. Benton E. Wetzel and Frank A. PfyL 
January 1954. 35p. diagrs., photo., tabs. 
(NACA RM A53J14a) 



A FLIGHT INVESTIGATION AT TRANSONIC SPEEDS 
OF THE AERODYNAMIC CHARACTERISTICS OF A 
MODEL HAVING A THIN UNSWEPT WING OF 
ASPECT RATIO 3.1. Maurice D. White. August 
1954. 4lp. diagrs., photo., tabs. 
(NACA RM A54E12) 



AN EXPERIMENTAL INVESTIGATION OF REDUC- 
TION IN TRANSONIC DRAG RISE AT ZERO LIFT BY 
THE ADDITION OF VOLUME TO THE FUSELAGE 
OF A WING -BODY -TAIL CONFIGURATION AND A 
COMPARISON WITH THEORY. George H. Holdaway. 
August 1954. 35p. diagrs., photos., tabs. 
(NACA RM A54F22) 



EFFECTS OF CANOPY, REVISED VERTICAL TAIL, 
AND A YAW-DAMPER VANE ON THE AERODYNAM- 
IC CHARACTERISTICS OF A 1/16-SCALE MODEL 
OF THE DOUGLAS D-558-H RESEARCH AIRPLANE 
AT A MACH NUMBER OF 2.01. Ross B. Robinson. 
August 1954. 29p. diagrs., tabs. 
(NACA RM L54F25) 



LOW -SPEED MEASUREMENT OF STATIC STABIL- 
ITY AND DAMPING DERIVATIVES OF A 60° 
DELTA-WING MODEL FOR ANGLES OF ATTACK 
OF 0° TO 90°. Donald E. Hewes. September 1954. 
30p. diagrs., photo., tab. (NACA RM L54G22a) 



THE EFFECT OF AN OPERATING PROPELLER ON 
THE AERODYNAMIC CHARACTERISTICS AT HIGH 
SUBSONIC SPEEDS OF A MODEL OF A VERTICAL- 
RISING AIRPLANE HAVING AN UNSWEPT WING OF 
ASPECT RATIO 3. Fred B. Sutton and Donald A. 
Buell. November 1954. 90p. diagrs., photos., 
tabs. (NACA RM A52E06) 



LIFT AND DRAG CHARACTERISTICS OF THE 
DOUGLAS X-3 RESEARCH AIRPLANE OBTAINED 
DURING DEMONSTRATION FLIGHTS TO A MACH 
NUMBER OF 1.20. Donald R. Bellman and 
Edward D. Murphy. December 1954. 23p. diagrs., 
photos., tab. (NACA RM H54I17) 



LOW-SPEED MEASUREMENTS OF ROLLING AND 
YAWING STABILITY DERIVATIVES OF A 60° 
DELTA-WING MODEL. Joseph L. Johnson, Jr. 
December 1954. 17p. diagrs., tab. 
(NACA RM L54G27) 



A FLIGHT INVESTIGATION AT TRANSONIC 
SPEEDS AND SMALL ANGLES OF ATTACK OF THE 
AERODYNAMIC CHARACTERISTICS OF A MODEL 
HAVING A 450 SWEPTBACK WING OF ASPECT 
RATIO 3 WITH AN NACA 64A006 AIRFOIL SECTION. 
George H. Holdaway. January 1955. 32p. diagrs., 
photo., tab. (NACA RM A54I17) 



LONGITUDINAL STABILITY CHARACTERISTICS 
AT MACH NUMBERS UP TO 0.92 OF A WING- 
BODY-TAIL COMBINATION HAVING A WING WITH 
45° OF SWEEPBACK AND A TAIL IN VARIOUS 
VERTICAL POSITIONS. Jack D. Stephenson, 
Angel o Bandettini, and Ralph Selan. January 1955. 
64p. diagrs., photos., tabs. (NACA RM A54K09) 



INVESTIGATION OF THE LATERAL STABILITY 
CHARACTERISTICS OF THE DOUGLAS X-3 CON- 
FIGURATION AT MACH NUMBERS FROM 0.6 TO 
1.1 BY MEANS OF A ROCKET -PROPELLED 
MODEL. Jesse L. Mitchell and Robert F. Peck. 
February 1955. 37p. diagrs., photo., tabs. 
(NACA RM L54L20) 



THE LONGITUDINAL CHARACTERISTICS AT MACH 
NUMBERS UP TO 0.92 OF SEVERAL WING- 
FUSELAGE-TAIL COMBINATIONS HAVING SWEPT- 
BACK WINGS WITH NACA FOUR-DIGIT THICKNESS 
DISTRIBUTIONS. Fred B. Sutton and Jerald K. 
Dickson. March 1955. 128p. diagrs., photos., tab. 
(NACA RM A54L08) 

A FLIGHT INVESTIGATION AT TRANSONIC SPEEDS 
OF A MODEL HAVING A TRIANGULAR WING OF 
ASPECT RATIO 4. Loren G. Bright. March 1955. 
40p. diagrs., photos., tabs. (NACA RM A54L27) 



LATERAL STABILITY CHARACTERISTICS AT LOW 
LIFT BETWEEN MACH NUMBERS OF 0.85 AND 1.15 
OF A ROCKET -PROPELLED MODEL OF A SUPER- 
SONIC AIRPLANE CONFIGURATION HAVING A 
TAPERED WING WITH CIRCULAR -ARC SECTIONS 
AND 4CP SWEEPBACK. Charles T. D'Aiutolo and 
Allen B. Henning. April 1955. 50p. diagrs., 
photos., tabs. (NACA RM L55A31) 



LIFT, DRAG, AND LONGITUDINAL STABILITY AT 
MACH NUMBERS FROM 0.8 TO 2.1 OF A ROCKET- 
POWERED MODEL HAVING A TAPERED UNSWEPT 
WING OF ASPECT RATIO 3 AND INLINE TAIL 
SURFACES. Warren Gillespie, Jr. April 1955. 
29p. diagrs., photo., tabs. (NACA RM L55B10) 



A COMPARISON AT MACH NUMBERS UP TO 0.92 
OF THE CALCULATED AND EXPERIMENTAL 
DOWNWASH AND WAKE CHARACTERISTICS AT 
VARIOUS HORIZONTAL TAIL HEIGHTS BEHIND A 
WING WITH 450 OF SWEEPBACK. Jack D. 
Stephenson, Ralph Selan, and Angelo Bandettini. 
June 1955. Sip. diagrs., photos., tabs. 
(NACA RM A55D27a) 



ADDITIONAL MEASUREMENTS OF THE LOW- 
SPEED STATIC STABILITY OF A CONFIGURATION 
EMPLOYING THREE TRIANGULAR WING PANELS 
AND A BODY OF EQUAL LENGTH. Noel K. Delany. 
July 1955. 3Ip. diagrs. (NACA RM A55F02a) 

STABILITY AND CONTROL CHARACTERISTICS 
OBTAINED DURING DEMONSTRATION OF THE 
DOUGLAS X-3 RESEARCH AIRPLANE. Richard E. 
Day and Jack Fischel. July 1955. 51p. diagrs., 
photos., tab. (NACA RM H55E16) 



115 



(1) AERODYNAMICS 



INVESTIGATION AT HIGH SUBSONIC SPEEDS OF 
THE EFFECTS OF VARIOUS UNDERWING 
EXTERNAL-STORE ARRANGEMENTS ON THE 
AERODYNAMIC CHARACTERISTICS OF A 1/16- 
SCALE MODEL OF THE DOUGLAS D-558-I1 
RESEARCH AIRPLANE. H. Norman Silvers and 
Thomas J. King, Jr. July 1955. 59p. dlagrs., 
photos., tab. (NACA RM L55D11) 



ADDITIONAL COMPARISONS BETWEEN COMPUTED 
AND MEASURED TRANSONIC DRAG-RISE COEFFI- 
CIENTS AT ZERO LIFT FOR WING-BODY-TAIL 
CONFIGURATIONS. George H. Holdaway. August 

1955. 43p. diagrs., photo., tabs. 
(NACA RM A55F06) 



SUMMARY AND ANALYSIS OF HORIZONTAL-TAIL 
CONTRIBUTION TO LONGITUDINAL STABILITY OF 
SWEPT -WING AIRPLANES AT LOW SPEEDS. 
Robert H. Neely and Roland F. Griner. August 1955. 
ii, 133p. diagrs., tabs. (NACA RM L55E23a) 



A FLIGHT INVESTIGATION AT TRANSONIC SPEEDS 
OF A MODEL HAVING A TRIANGULAR WING OF 
ASPECT RATIO 2. Maurice D. White. September 
1955. 39p. diagrs., photo., tabs. 
(NACA RM A55F21) 



INVESTIGATION AT HIGH SUBSONIC SPEEDS OF 
THE STATIC LONGITUDINAL STABILITY CHARAC- 
TERISTICS OF A MODEL HAVING CROPPED-DELTA 
AND UNSWEPT WING PLAN FORMS AND SEVERAL 
TAIL CONFIGURATIONS. Albert G. Few, Jr. 
November 1955. 107p. diagrs., photo., tab. 
(NACA RM L55l23a) 



THE EFFECT OF LEADING-EDGE EXTENSIONS 
OF THE LONGITUDINAL CHARACTERISTICS AT 
MACH NUMBERS UP TO 0.92 OF A WING- 
FUSELAGE-TAIL COMBINATION HAVING A 40° 
SWEPTBACK WING WITH NACA 64 A THICKNESS 
DISTRIBUTION. Fred B. Sutton. January 1956. 
52p. diagrs., photos., tabs. (NACA RM A55I29) 



AN INVESTIGATION OF THE AERODYNAMIC CHAR- 
ACTERISTICS AT TRANSONIC MACH NUMBERS OF 
A SWEPT-WTNG SUPERSONIC BOMBER CONFIGU- 
RATION. Ralph P. BielatandJ. Lawrence Cooper. 
February 1956. 92p. diagrs., photos., tabs. 
(NACA RM L53F05) 



WIND-TUNNEL INVESTIGATION AT HIGH SUBSONIC 
SPEEDS OF SOME EFFECTS OF FUSELAGE CROSS- 
SECTION SHAPE AND WING HEIGHT ON THE STAT- 
IC LONGITUDINAL AND LATERAL STABILITY 
CHARACTERISTICS OF A MODEL HAVING A 45° 
SWEPT WING. Thomas J. King, Jr. February 
1956. 61p. diagrs., photo. (NACA RM L55J25) 



EXPERIMENTAL INVESTIGATION AT HIGH SUB- 
SONIC SPEED OF THE ROLLING STABILITY 
DERIVATIVES OF A COMPLETE MODEL HAVING 
A CLD7PED-DELTA WING AND A HIGH HORIZON- 
TAL TAIL. William C. Sleeman, Jr., and Albert G. 
Few, Jr. February 1956. 32p. diagrs., tab. 
(NACA RM L55K11) 



SOME EFFECTS OF AILERONS ON THE VARIATION 
OF AERODYNAMIC CHARACTERISTICS WITH SIDE- 
SLIP AT LOW SPEED. Kenneth W. Goodsoa. 
March 1956. 4 Op. diagrs., tab. (NACA RM L55L20) 



FLIGHT MEASUREMENTS OF HORIZONTAL -TAIL 
LOADS ON THE DOUGLAS X-3 RESEARCH AIR- 
PLANE. Harriet J. Stephenson. April 1956. 33p. 
diagrs., photo., tab. (NACA RM H56A23) 



LOW-SPEED INVESTIGATION OF THE EFFECTS 
OF WING DIHEDRAL ANGLE AND FIN LENGTH ON 
THE STATIC STABILITY CHARACTERISTICS OF A 
MODEL HAVING AN 82° DELTA WING. Kenneth P. 
Spreemann. April 1956. 30p. diagrs. 
(NACA RM L55L30a) 



AN EXPERIMENTAL STUDY AT HIGH SUBSONIC 
SPEEDS OF SEVERAL TAIL CONFIGURATIONS ON 
A MODEL WITH AN UNSWEPT WING . William C . 
Sleeman, Jr. April 1956. 67p. diagrs., photos. 
(NACA RM L56A06a) 



LATERAL STABILITY CHARACTERISTICS BE- 
TWEEN MACH NUMBERS OF 0.80 AND 1.57 AND 
SIMULATION OF COUPLED MOTION AT MACH 
NUMBER 1.30 OF A ROCKET-PROPELLED MODEL 
OF AN AIRPLANE CONFIGURATION HAVING THIN 
HIGHLY TAPERED 45° SWEPTBACK SURFACES. 
Charles T. D'Aiutolo and Allen B. Henning. April 
1956. 41p. diagrs., photos., tabs. 
(NACA RM L56A17) 



INVESTIGATION AT HIGH SUBSONIC SPEEDS OF 
THE EFFECT OF HORIZONTAL -TAIL LOCATION 
ON LONGITUDINAL AND LATERAL STABILITY 
CHARACTERISTICS OF A COMPLETE MODEL 
HAVING A SWEPTBACK WING IN A HIGH LOCA- 
TION. H. Norman Silvers and Thomas J. King, Jr. 
April 1956. 46p. diagrs., tab. (NACA RM L56B10) 



DATA FROM LARGE-SCALE LOW-SPEED TESTS 
OF AIRPLANE CONFIGURATIONS WITH A THIN 45° 
SWEPT WING INCORPORATING SEVERAL 
LEADING-EDGE CONTOUR MODIFICATIONS. 
William T. Evans. May 1956. HOp. diagrs., 
photo., tabs. (NACA RM A56B17) 



A HORIZONTAL -TAIL ARRANGEMENT FOR 
COUNTERACTING STATIC LONGITUDINAL 
INSTABILITY OF SWEPTBACK WINGS. George G. 
Edwards and Howard F. Savage. May 1956. 51p. 
diagrs., photos., tab. (NACA RM A56D06) 



EFFECT OF AIRPLANE CONFIGURATION ON 
STATIC STABILITY AT SUBSONIC AND TRANSONIC 
SPEEDS. Edward C Polhamus and Joseph M. 
Hallissy, Jr. May 1956. 17p. diagrs. 
(NACARML56A09a) 



EFFECT OF WING CAMBER AND TWIST AT MACH 
NUMBERS FROM 1.4 TO 2.1 ON THE LIFT, DRAG, 
AND LONGITUDINAL STABILITY OF A ROCKET- 
POWERED MODEL HAVING A 52.5° SWEPTBACK 
WING OF ASPECT RATIO 3 AND INLINE TAIL SUR- 
FACES. Warren Gillespie, Jr. May 1956. 29p. 
diagrs., photos., tabs. (NACA RM L56C16) 



LOW-SPEED WIND-TUNNEL RESULTS FOR A THIN 
ASPECT-RATIO-1.85 POINTED-WING-FUSELAGE 
MODEL WITH DOUBLE SLOTTED FLAPS. Albert 
E. Brown. July 1956. 31p. diagrs., tabs. 
(NACA RM L56D03) 



EFFECT OF WING HEIGHT AND DIHEDRAL ON THE 
LATERAL STABILITY CHARACTERISTICS AT LOW 
LIFT OF A 45° SWEPT -WING AIRPLANE CONFIG- 
URATION AS OBTAINED FROM TIME-VECTOR 
ANALYSES OF ROCKET-PROPELLED-MODEL 
FLIGHTS AT MACH NUMBERS FROM 0.7 TO 1.3. 
Clarence L. Gillis and Rowe Chapman, Jr. 
September 1956. 70p. diagrs., photos., tabs. 
(NACA RM L56E17) 



116 



(1) AERODYNAMICS 



WIND-TUNNEL INVESTIGATION OF THE DAMPING 
IN ROLL OF THE DOUGLAS D-558-H RESEARCH 
AIRPLANE AND ITS COMPONENTS AT SUPERSONIC 
SPEEDS. Russell W. McDearmon. September 1956. 
36p. diagrs., photos. (NACA RM L56F07) 



STATIC STABILITY CHARACTERISTICS OF A 
CAMBERED-DELTA-WING MODEL AT HIGH 
SUBSONIC SPEEDS. William C. Moseley, Jr. 
October 1956. 35 p. diagrs., photos. 
(NACA RML56H13) 



COMBINED EFFECTS OF WING TAPER RATIO AND 
LOW HORIZONTAL -TAIL POSITION ON LONGITU 
DINAL STABILITY OF A 45° SWEPTBACK WING- 
BODY COMBINATION AT TRANSONIC SPEEDS. 
Stanley H. Spooner. October 1956. 28p. diagrs., 
tab. (NACA RM L56H24) 



ANALYSIS OF THE VERTICAL-TAIL LOADS MEAS- 
URED DURING A FLIGHT INVESTIGATION AT 
TRANSONIC SPEEDS OF THE DOUGLAS X-3 RE- 
SEARCH AIRPLANE . William L. Marcy, Harriet J . 
Stephenson, and Thomas V. Cooney. November 1956. 
32p. diagrs., photo., tab. (NACA RM H56H08) 



LOW -SPEED MEASUREMENT OF TAIL CONTRI- 
BUTION TO ROLLING STABILITY DERIVATIVES 
AND AIR-FLOW ANGULARITY AT THE TAIL FOR 
AN X-TAIL MODEL IN STEADY ROLL INCLUDING 
SOME EFFECTS OF WING-TD? STORES. Donald R. 
Riley. November 1956. 28p. diagrs., photo., tab. 
(NACA RM L56I21) 



FORCE TEST RESULTS FOR BODY-MOUNTED 
LATERAL CONTROLS AND SPEED BRAKES ON A 
45° SWEPT-WING MODEL AT MACH NUMBERS 
FROM 0.80 TO 0.98. F. E. West, Jr., and Chris C. 
Critzos. December 1956. 32p. diagrs., photos., 
tab. (NACA RM L56I05) 



LIFT AND CENTER OF PRESSURE OF WING-BODY- 
TAIL COMBINATIONS AT SUBSONIC, TRANSONIC, 
AND SUPERSONIC SPEEDS. William C. Pitts, Jack 
N. Nielsen, and George E. Kaattari. 1957. ii, 70p. 
diagrs., tabs. (NACA Rept. 1307) 



A SUMMARY AND ANALYSIS OF THE LOW-SPEED 
LONGITUDINAL CHARACTERISTICS OF SWEPT 
WINGS AT HIGH REYNOLDS NUMBER. G. Chester 
Furlong and James G. McHugh. 1957. ill, 14 9p. 
diagrs., tabs. (NACA Rept. 1339. Supersedes 
RM L52D16) 



STATIC LONGITUDINAL CHARACTERISTICS AT 
HIGH SUBSONIC SPEEDS OF A COMPLETE AIR- 
PLANE MODEL WITH A HIGHLY TAPERED WING 
HAVING THE 0.80 CHORD LINE UNSWEPT AND 
WITH SEVERAL TAIL CONFIGURATIONS. Kenneth 
W. Goodson. January 1957. 57p. diagrs., photo., 
tabs. (NACA RM L56J03) 



THE SUBSONIC STATIC AERODYNAMIC CHARAC- 
TERISTICS OF AN AIRPLANE MODEL HAVING A 
TRIANGULAR WING OF ASPECT RATIO 3. I - EF- 
FECTS OF HORIZONTAL-TAB^ LOCATION AND 
SIZE ON THE LONGITUDINAL CHARACTERISTICS. 
Bruce E. Tlnllng and Armando E. Lopez. July 1957. 
85p. diagrs., photo., tabs. (NACA TN 4041. Super- 
sedes RM A53L1 5) 



GROUND EFFECTS ON THE LONGITUDINAL CHAR- 
ACTERISTICS OF TWO MODELS WITH WINGS 
HAVING LOW ASPECT RATIO AND POINTED TIPS. 
Donald A. Buell and Bruce E . Tlnllng. July 1957. 
48p. diagrs., photos., tabs. (NACA TN 4044. 
Supersedes RM A55E04) 



EFFECT OF FREQUENCY OF SIDESLIPPING 
MOTION ON THE LATERAL STABILITY DERIVA- 
TIVES OF A TYPICAL DELTA-WING AIRPLANE. 
Jacob H. Lichtenstein and James L. Williams. 
September 1957. . 46p. diagrs., photos., tabs. 
(NACA RM L57F07) 



WIND-TUNNEL INVESTIGATION AT LOW SPEEDS 
TO DETERMINE FLOW-FIELD CHARACTERISTICS 
AND GROUND INFLUENCE ON A MODEL WITH 
JET-AUGMENTED FLAPS. Raymond D. Vogler and 
Thomas R. Turner. September 1957. 48p. diagrs., 
photos. (NACA TN 4116) 



WIND-TUNNEL INVESTIGATION OF EFFECTS OF 
GROUND PROXIMITY AND OF SPLIT FLAPS ON 
THE LATERAL STABILITY DERIVATIVES OF A 60° 
DELTA-WING MODEL OSCILLATING IN YAW. 
Byron M. Jaquet. September 1957. 32p. diagrs. 
photos., tab. (NACA TN 4119) 



WIND-TUNNEL INVESTIGATION OF THE STATIC 
LONGITUDINAL STABILITY AND TRIM CHARAC- 
TERISTICS OF A SWEPTBACK-WING JET- 
TRANSPORT MODEL EQUIPPED WITH AN 
EXTERNAL-FLOW JET-AUGMENTED FLAP. 
Joseph L. Johnson, Jr. January 1958. 89p. 
diagrs., tab. (NACA TN 4177) 



EFFECTS OF FIXING BOUNDARY- LAYER TRANSI- 
TION FOR AN UNSWEPT -WING MODEL AND AN 
EVALUATION OF POROUS TUNNEL-WALL INTER- 
FERENCE FOR MACH NUMBERS FROM 0.60 TO 
1.40. Louis S. Stivers, Jr., and Garth W.. Lippmann. 
April 1958. 37p. diagrs. (NACA TN 4228) 



DATA FROM FLOW-FIELD SURVEYS BEHIND A 
LARGE-SCALE THIN STRAIGHT WING OF ASPECT 
RATIO 3. William T. Evans. June 1958. 13p. 
diagrs. (NACA RM A58D17) 



A NUMERICAL METHOD FOR EVALUATING WAVE 
DRAG. Maurice S. Cahn and Waiter B. Olstad. 
June 1958. 13p. diagrs., tabs. (NACA TN 4258) 



WIND-TUNNEL INVESTIGATION AT LOW SPEEDS 
OF FLIGHT CHARACTERISTICS OF A SWEPTBACK- 
WING JET-TRANSPORT AIRPLANE MODEL . 
EQUIPPED WITH AN EXTERNAL-FLOW JET- 
AUGMENTED SLOTTED FLAP. Joseph L. Johnson, 
Jr. July 1958. 32p. diagrs., photos., tab., film 
suppl. available on request. (NACA TN 4255) 



SOME FACTORS AFFECTING THE VARIATION OF 
PITCHING MOMENT WITH SIDESLIP OF AIRCRAFT 
CONFIGURATIONS. Edward C. Polhamus. August 
1958. 35p. diagrs., photo. (NACA TN 4016. 
Supersedes RM L55E20b) 



EFFECTS OF FREQUENCY AND AMPLITUDE ON 
THE YAWING DERIVATIVES OF TRIANGULAR, 
SWEPT, AND UNSWEPT WINGS AND OF A 
TRIANGULAR-WING-FUSELAGE COMBINATION 
WITH AND WITHOUT A TRIANGULAR TAIL PER- 
FORMING SINUSOIDAL YAWING OSCILLATIONS. 
William Letko and Herman S. Fletcher. September 
1958. 52p. diagrs., photos., tabs. (NACA TN 4390) 



STATIC LONGITUDINAL AND LATERAL STABILITY 
CHARACTERISTICS AT LOW SPEED OF 60° 
SWEPTBACK-MIDWING MODELS HAVING WINGS 
WITH AN ASPECT RATIO OF 2, 4, OR 6. Walter D. 
Wolhart and David F. Thomas, Jr. September 1958. 
41p. diagrs., tabs. (NACA TN 4397) 



117 



(1) AERODYNAMICS 



(1.7-1- 1-4) 
Propeller and Jet Interference 



THE EFFECT OF AN OPERATING PROPELLER ON 
THE AERODYNAMIC CHARACTERISTICS AT HIGH 
SUBSONIC SPEEDS OF A MODEL OF A VERTICAL- 
RISING AIRPLANE HAVING AN UNSWEPT WING OF 
ASPECT RATIO 3. Fred B. Sutton and Donald A. 
Buell. November 1954. 90p. diagrs., photos., 
tabs. (NACA RM A52E06) 



(1.7.1.1.5) 
Stores 



FLIGHT TESTS OF A MODEL HAVING SELF- 
SUPPORTING FUEL-CARRYING PANELS HINGED 
TO THE WING TIPS . Robert E. Shanks and David C. 
Grana. November 2, 1949. lOp. diagrs., tab. 
(NACA RM L9I07a) 



WIND-TUNNEL TESTS OF A 0.16-SCALE MODEL 
OF THE X-3 AIRPLANE AT HIGH SUBSONIC SPEEDS. 
- ADDITIONAL STABILITY AND CONTROL CHAR- 
ACTERISTICS AND THE AERODYNAMIC EFFECTS 
OF EXTERNAL STORES AND RAM JETS. Joseph W. 
Cleary and Jack A. Mellenthin. June 13, 1950. 86p. 
diagrs., photos., tabs. (NACA RM A50C30) 



INVESTIGATION OF THE AERODYNAMIC EFFECTS 
OF AN EXTERNAL STORE IN COMBINATION WITH 
60° DELTA AND LOW-ASPECT -RATIO TAPERED 
WINGS AT A MACH NUMBER OF 1 .9. Ellery B. 
May, Jr. January 9, 1951. 46p. diagrs., photos. 
(NACA RM L5OK03) 



FREE -FLIGHT -TUNNEL INVESTIGATION OF THE 
DYNAMIC LATERAL STABILITY AND CONTROL 
CHARACTERISTICS OF A HIGH -ASPECT -RATIO 
BOMBER MODEL WITH SELF-SUPPORTING FREE- 
FLOATING FUEL TANKS ATTACHED TO THE WING 
TIPS. Charles V. Bennett and Robert B. Cadman. 
August 1951. 12p. diagrs., tab. (NACA RM L51E17) 



AERODYNAMIC CHARACTERISTICS AT SUPER- 
SONIC SPEEDS OF A SERIES OF WING-BODY 
COMBINATIONS HAVING CAMBERED WINGS WITH 
AN ASPECT RATIO OF 3.5 AND A TAPER RATIO 
OF 0.2. EFFECT AT M = 1.60 OF NACELLE 
SHAPE AND POSITION ON THE AERODYNAMIC 
CHARACTERISTICS IN PITCH OF TWO WING-BODY 
COMBINATIONS WITH 47° SWEPTBACK WINGS. 
Lowell E. Hasel and John R. Sevier, Jr. January 
1952. 31p. diagrs., photos., tabs. 
(NACA RML51K14a) 



AERODYNAMIC CHARACTERISTICS AT SUPER- 
SONIC SPEEDS OF A SERIES OF WING-BODY COM- 
BINATIONS HAVING CAMBERED WINGS WITH AN 
ASPECT RATIO OF 3.5 AND A TAPER RATIO OF 
0.2. EFFECT AT M = 2.01 OF NACELLE SHAPE 
AND POSITION ON THE AERODYNAMIC CHARAC- 
TERISTICS IN PITCH OF TWO WING-BODY COM- 
BINATIONS WITH 47° SWEPTBACK WINGS. 
Cornelius Driver. July 1952. 27p. diagrs., photos., 
tab. (NACA RM L52F03) 



EFFECTS OF SYSTEMATICALLY VARYING THE 
SPANWISE AND VERTICAL LOCATION OF AN EX- 
TERNAL STORE ON THE AERODYNAMIC CHARAC- 
TERISTICS OF AN UNSWEPT TAPERED WING OF 
ASPECT RATIO 4 AT MACH NUMBERS OF 1.41, 
1.62, AND 1.96. Carl R. Jacobsen. August 1952. 
34p. diagrs. (NACA RM L52F13) 



FREE -FLIGHT -TUNNEL INVESTIGATION OF THE 
DYNAMIC LATERAL STABILITY AND CONTROL 
CHARACTERISTICS OF A HIGH-ASPECT-RATIO 
BOMBER MODEL WITH A SWEPT BACK -WING 
FIGHTER MODEL ATTACHED TO EACH WING TIP. 
Charles V. Bennett and Peter C. Boisseau. 
September 1952. 17p. diagrs., tabs. 
(NACA RM L52E08) 



A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF NACELLE SHAPE AND POSITION 
ON THE AERODYNAMIC CHARACTERISTICS OF 
TWO 47° SWEPTBACK WING-BODY CONFIGURA- 
TIONS. Ralph P. Bielat and Daniel E. Harrison. 
September 1952. 87p. diagrs., photos., tab. 
(NACA RM L52G02) 



EXPLORATORY ROCKET FLIGHT TESTS TO IN- 
VESTIGATE THE USE OF A FREELY SPINNING 
MONOPLANE TAIL FOR STABILIZING A BODY. 
Paul E. Purser and Joseph E. Stevens. October 
1952. 25p. diagrs., photos., tab. 
(NACA RM L52I05a) 

INVESTIGATION AT HIGH SUBSONIC SPEEDS OF 
BODffiS MOUNTED FROM THE WING OF AN 
UNSWEPT-WING-FUSELAGE MODEL, INCLUDING 
MEASUREMENTS OF BODY LOADS. H. Norman 
Silvers and Thomas J. King, Jr. November 1952. 
37p. diagrs., photos., tabs. (NACA RM L52J08) 



EFFECTS OF THE SPANWISE, CHORDWISE, AND 
VERTICAL LOCATION OF AN EXTERNAL STORE 
ON THE AERODYNAMIC CHARACTERISTICS OF A 
45° SWEPTBACK TAPERED WING OF ASPECT 
RATIO 4 AT MACH NUMBERS OF 1.41, 1.62, AND 
1.96. CarlR. Jacobsen. January 1953. 31p. 
diagrs., photo. (NACA RM L52J27) 



EFFECTS OF SIZE OF EXTERNAL STORES ON THE 
AERODYNAMIC CHARACTERISTICS OF AN UN- 
SWEPT AND A 45° SWEPTBACK WING OF ASPECT 
RATIO 4 AND A 60° DELTA WING AT MACH NUM- 
BERS OF 141, 1.62, AND 1.96. Carl R. Jacobsen. 
January 1953. 55p. diagrs., photos., tab. 
(NACA RM L52K20a) 



THE EFFECT OF NACELLE COMBINATIONS AND 
SIZE ON THE ZERO-LIFT DRAG OF A 45° SWEPT- 
BACK WING AND BODY CONFIGURATION AS DE- 
TERMINED BY FREE-FLIGHT TESTS AT MACH 
NUMBERS BETWEEN 0.8 AND 1.3. Sherwood 
Hoffman and William B. Pepper, Jr. June 1953. 
22p. diagrs., photos., tabs. (NACARM L53E25) 



INVESTIGATION OF THE EFFECT OF SPANWISE 
POSITIONING OF A VERTICALLY SYMMETRIC 
OGIVE -CYLINDER NACELLE ON THE HIGH-SPEED 
AERODYNAMIC CHARACTERISTICS OF A 45° 
SWEPTBACK TAPERED-rN-THTCKNESS WING OF 
ASPECT RATIO 6 WITH AND WITHOUT A FUSE- 
LAGE . H. Norman Silvers and Thomas J. King, Jr. 
October 1953. 62p. diagrs., tabs. 
(NACA RM L53H17) 



WIND-TUNNEL INVESTIGATION AT HIGH SUBSONIC 
SPEEDS OF THE EFFECTS OF WING-MOUNTED 
EXTERNAL STORES ON THE LOADING AND AERO- 
DYNAMIC CHARACTERISTICS IN PITCH OF A 45° 
SWEPTBACK WING COMBINED WITH A FUSELAGE. 
H. Norman Silvers, Thomas J. King, Jr., and 
William J. AUord, Jr. March 1954. 36p. diagrs., 
tabs. (NACA RM L54A21) 



THE EFFECT OF NACELLE LOCATION ON THE 
ZERO-LIFT DRAGS OF 45° SWEPTBACK WING- 
BODY CONFIGURATIONS HAVING BOATTAIL AND 
CYLINDRICAL AFTERBODIES AS DETERMINED BY 
FLIGHT TESTS AT TRANSONIC SPEEDS. Sherwood 
Hoffman and Austin L. Wolff. March 1954. 29p. 
diagrs., photos., tabs. (NACA RM L54B02) 



118 



(1) AERODYNAMICS 



INVESTIGATION AT HIGH SUBSONIC SPEEDS OF 
FINNED AND UNFINNED BODIES MOUNTED AT 
VARIOUS LOCATIONS FROM THE WINGS OF UN- 
SWEPT, AND SWEPT-WING-FUSELAGE MODELS, 
INCLUDING MEASUREMENTS OF BODY LOADS. 
William J. Alford, Jr., and H. Norman Silvers. 
April 1954. 93p. diagrs., photos., tabs. 
(NACA RM L54B18) 



THE EFFECTS OF WING-MOUNTED EXTERNAL 
STORES ON THE TRIM, BUFFET, AND DRAG 
CHARACTERISTICS OF A ROCKET -PROPELLED 
MODEL HAVING A 45° SWEPTBACK WING. Allen B. 
uiagrt*., photos., tabs. 



(NACA RM L54B19) 



«up. 



INVESTIGATION AT HIGH SUBSONIC SPEEDS OF 
THE EFFECT OF ADDING VARIOUS COMBINATIONS 
OF MISSILES ON THE AERODYNAMIC CHARACTER- 
ISTICS OF SWEPTBACK AND UNSWEPT WINGS 
COMBINED WITH A FUSELAGE. H. Norman 
Silvers and William J. Alford, Jr. June 1954. 39p. 
diagrs., photo., tabs. (NACA RM L54D20) 



EXPLORATORY INVESTIGATION OF EXTERNAL 
STORES ON THE AERODYNAMIC CHARACTERIS- 
TICS OF A l/16-SCALE MODEL OF THE DOUGLAS 
D-558-II RESEARCH AIRPLANE AT A MACH NUM- 
BER OF 2.01. Norman F. Smith. August 1954. 
25p. diagrs., photos. (NACA RM L54F02) 



EFFECTS OF SOME EXTERNAL-STORE MOUNTING 
ARRANGEMENTS AND STORE SHAPES ON THE 
BUFFET AND DRAG CHARACTERISTICS OF WING- 
LESS ROCKET-POWERED MODELS AT MACH NUM- 
BERS FROM 0.7 TO 1.4. Homer P. Mason and 
Allen B. Henning. December 1954. 45p. diagrs., 
photos., tabs. (NACA RM L54I20a) 



PRELIMINARY LOW-SPEED WIND-TUNNEL INVES- 
TIGATION OF SOME ASPECTS OF THE AERODY- 
NAMIC PROBLEMS ASSOCIATED WITH MISSILES 
CARRIED EXTERNALLY IN POSITIONS NEAR AIR- 
PLANE WINGS. William J. Alford, Jr., H. Norman 
Stivers, and Thomas J. King, Jr. December 1954. 
30p. diagrs., photos., tab. (NACA RM L54J20) 



FLUTTER INVESTIGATION OF A TRUE -SPEED 
DYNAMIC MODEL WITH VARIOUS TIP-TANK 
CONFIGURATIONS. John L. Sewatl, Robert W. 
Herr, and William B. Igoe. March 1955. 80p. 
diagrs,, photos., tabs. (NACA RM L 541 19) 



INVESTIGATION AT HIGH SUBSONIC SPEEDS OF 
THE EFFECTS OF VARIOUS UNDERWING 
EXTERNAL-STORE ARRANGEMENTS ON THE 
AERODYNAMIC CHARACTERISTICS OF A 1/16- 
SCALE MODEL OF THE DOUGLAS D-558-II 
RESEARCH AIRPLANE. H. Norman Silvers and 
Thomas J. King, Jr. July 1955. 59p. diagrs., 
photos., tab. (NACARM L55D11) 



FLIGHT MEASUREMENTS OF THE LOADS AND 
MOMENTS ON AN EXTERNAL STORE MOUNTED 
UNDER THE WING OF A SWEPT-WING FIGHTER- 
TYPE AIRPLANE DURING YAWING AND ROLLING 
MANEUVERS. Harold A. Hamer and Thomas C. 
O'Bryan. September 1955. 37p. diagrs., photo., 
tab. (NACA RM L55G22) 



AERODYNAMIC LOADS ON AN EXTERNAL STORE 
ADJACENT TO A 45° SWEPTBACK WING AT MACH 
NUMBERS FROM 0.70 TO 1.96, INCLUDING AN 
EVALUATION OF TECHNIQUES USED. Lawrence 
D. Guy and William M. Hadaway. November 1955. 
109p. diagrs., photo., tab. (NACA RM L55H12) 



TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF EXTERNAL STORES AND STORE 
POSITION ON THE AERODYNAMIC CHARACTERIS- 
TICS OF A 1/16-SCALE MODEL OF THE DOUGLAS 
D-558-II RESEARCH AIRPLANE. Thomas C. Kelly. 
November 1955. 31p. diagrs., photos., tab. 
(NACA RM L55I07) 



INVESTIGATION AT HIGH SUBSONIC SPEEDS OF 
SOME EFFECTS OF SIDESLIP ON THE AERODY- 
NAMIC LOADS ON FINNED AND UNFINNED BODDSS 
MOUNTED FROM THE WING OF A SWEPT -WING- 
FUSELAGE MODEL. Thomas J. King, Jr. April 



1Q*A 



*n« 






JUA^t) 



A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
STORE AND HORIZONTAL-TAIL LOADS AND SOME 
EFFECTS OF FUSELAGE-AFTERBODY MODIFICA- 
TIONS ON A SWEPT-WING FIGHTER AIRPLANE, 
Joseph M. Hallissy, Jr., and Louis Kudlac Ik. April 
1956. 79p. diagrs., photos. (NACA RM L56A26) 



WIND-TUNNEL MEASUREMENTS OF WING BUF- 
FETING ON 1/16-SCALE MODEL OF DOUGLAS 
D-558-II RESEARCH AIRPLANE. William B. Kemp, 
Jr., and Thomas J. King, Jr. September 1956.. 
34p. diagrs., photos., tabs. (NACA RM L56G31) 



LOW -SPEED MEASUREMENT OF TAIL CONTRI- 
BUTION TO ROLLING STABILITY DERIVATIVES 
AND AIR-FLOW ANGULARITY AT THE TAIL FOR 
AN X-TAIL MODEL IN STEADY ROLL INCLUDING 
SOME EFFECTS OF WrNG-TIP STORES. Donald R. 
Riley. November 1956. 28p. diagrs., photo., tab. 
(NACA RM L56I21) 



THEORETICAL CALCULATIONS OF SUPERSONIC 
WAVE DRAG AT ZERO LIFT FOR A PARTICULAR 
STORE ARRANGEMENT. Kenneth Margolis, 
Franks. Malvestuto, Jr., and Peter J. Maxie, Jr. 
January 1958. 37p. diagrs., tab. (NACA TN 4120) 



(1.7.1. 1.-6) 
Jet Interference 



SHAPE OF INITIAL PORTION OF BOUNDARY OF 
SUPERSONIC AXISYMMETRIC FREE JETS AT 
LARGE JET PRESSURE RATIOS. Eugene S. Love 
and Louise P. Lee. January 1958. 29p. diagrs. 
(NACA TN 4195) 



(1.7. 1.2) 
SPECIFIC AIRPLANES 



LONGITUDINAL STABILITY AND CONTRO! r'TAR- 
ACTERISTICS OF AN AffiPLANE MODEL HAVING A 
42.8° SWEPTBACK CIRCULAR- ARC WING WITH 
ASPECT RATIO 4.00, TAPER RATIO 0.50, AND 
SWEPTBACK TAIL SURFACES. Joseph Weil, Paul 
Comisarow, and Kenneth W. Goodson. October 17, 
1947. 84p. diagrs., photos., tab. 
(NACA RM L7G28) 

SUPERSONIC-TUNNEL TESTS OF TWO SUPER- 
SONIC AIRPLANE MODEL CONFIGURATIONS. 
Macon C. Ellis, Jr., Lowell E. Hasel, and Carl E 
Grigsby. December 31, 1947. 49p. diagrs., 
photos., tab. (NACA RM L7J15) 



WIND-TUNNEL INVESTIGATION OF THE STABILITY 
OF THE JETTISONABLE NOSE SECTION OF THE 
XS-2 AIRPLANE. Stanley H. Scher and Roscoe H. 
Goodwin. October 14, 1948. 19p. diagrs., photos., 
tabs. (NACA RM L8I14) 



119 



(1) AERODYNAMICS 



RESULTS OBTAINED DURING EXTENSION OF U.S. 
AIR FORCE TRANSONIC-FLIGHT TESTS OF XS-J 
AIRPLANE. Harold R. Goodman and Hubert M. 
Drake. November 16. 1948. 12p. diagrs. 
{NACA RM L8I28) 



DRAG MEASUREMENTS IN FLIGHT ON THE 
10-PERCENT-THICK AND 8-PERCENT-THICK 
WINGX-1 AIRPLANES. John J. Gardner. 
November 19, 1948. 17p. diagrs., photo. 
(NACA RM L8K05) 



AN INVESTIGATION IN THE LANGLEY 20- FOOT 
FREE-SPINNING TUNNEL OF THE SPIN AND RE- 
COVERY CHARACTERISTICS OF A l/30-SCALE 
MODEL OF THE BELL X-2 AIRPLANE. Lawrence 
J. Gale. July 20, 1949. 15p. diagrs., photo., tabs. 
{NACA RM L9G15a) 



ANALYSIS OF THE DYNAMIC- LATERAL -STABILITY 
CHARACTERISTICS OF THE BELL X-2 AIRPLANE 
AS AFFECTED BY VARIATIONS IN MASS, AERO- 
DYNAMIC, AND DIMENSIONAL PARAMETERS. 
W. H. -Michael, Jr., and M. J. Queijo. August 10, 
1949. 33p. diagrs., tabs. (NACA RM L9G13) 



WIND-TUNNEL TESTS OF A 0.16-SCALE MODEL 
OF THE X-3 AIRPLANE AT HIGH SUBSONIC 
SPEEDS. STABILITY AND CONTROL CHARACTER- 
ISTICS. William T. Hamilton and Joseph W. Cleary. 
April 21, 1950. 129p. diagrs., photos., tabs. 
fNACA nM iinifWi 



WIND-TUNNEL TESTS OF A 0.16-SCALE MODEL 
OF THE X-3 AIRPLANE AT HIGH SUBSONIC SPEEDS. 
- ADDITIONAL STABILITY AND CONTROL CHAR- 
ACTERISTICS AND THE AERODYNAMIC EFFECTS 
OF EXTERNAL STORES AND RAM JETS. Joseph W. 
Cleary and Jack A. Mellenthin. June 13, 1950. 86p. 
diagrs., photos., tabs. (NACA RM A50C30) 



WIND-TUNNEL TESTS OF A 0.16-SCALE MODEL 
OF THE X-3 AIRPLANE AT HIGH SUBSONIC SPEEDS. 
- WING AND FUSELAGE PRESSURE DISTRIBUTION. 
Joseph W. Cleary and Jack A. Mellenthin. June 22, 
1950. 6lp. diagrs., photos. (NACA RM A50D07) 



SUPPLEMENTARY ANALYSIS OF THE DYNAMIC 
LATERAL STABILITY CHARACTERISTICS OF THE 
BELL X-2 AIRPLANE AS AFFECTED BY VARIA- 
TIONS IN MASS AND AERODYNAMIC PARAMETERS. 
William H. Michael, Jr., andM. J. Queijo. 
June 26, 1950- 15p. diagrs. (NACA RM L50E08) 



FLIGHT MEASUREMENTS WITH THE DOUGLAS 
D-558-II (BUAERO NO. 37974) RESEARCH AIR- 
PLANE. DETERMINATION OF THE AERODYNAMIC 
CENTER AND ZERO-LIFT PITCHING-MOMENT 
COEFFICIENT OF THE WING-FUSELAGE COMBI- 
NATION BY MEANS OF TAIL-LOAD MEASURE- 
MENTS IN THE MACH NUMBER RANGE FROM 
0.37 TO 0.87. John P. Mayer, Ger.rge M. Valentine, 
and Geraldine C. Mayer. July 11, 1950. 27p. 
diagrs., photos., tab. (NACA RM L50D10) 



PRELIMINARY RESULTS OF THE FLIGHT INVES- 
TIGATION BETWEEN MACH NUMBERS OF 0.80 AND 
1.36 OF A ROCKET-POWERED MODEL OF A 
SUPERSONIC AIRPLANE CONFIGURATION HAVING 
A TAPERED WING WITH CIRCULAR-ARC SECTIONS 
AND 40<> SWEEPBACK. Charles T. D'Aiutolo and 
Homer P. Mason. October 31, 1950. 30p. diagrs., 
photos., tab. (NACA RM L50H29a) 



AN INVESTIGATION OF THE LONGITUDINAL 
CHARACTERISTICS OF THE X-3 CONFIGURATION 
USING ROCKET-PROPELLED MODELS. PRELIMI- 
NARY RESULTS AT MACH NUMBERS FROM 0.65 
TO 1.25. Jesse L. Mitchell and Robert F. Peck. 
December 1, 1950. 30p. diagrs., photos. 
(NACA RM L50J03) 



FLIGHT MEASUREMENTS WITH THE DOUGLAS 
D-558-II (BUAERO NO. 37974) RESEARCH AIR- 
PLANE. MEASUREMENTS OF WING LOADS AT 
MACH NUMBERS UP TO 0.87. John P. Mayer, 
George M. Valentine, and Beverly J. Swanson. 
December 26, 1950. 35p. diagrs., photos., tab. 
(NACA RM L50H16) 



FLIGHT -DETERMINED BUFFET BOUNDARIES OF 
TEN AIRPLANES AND COMPARISONS WITH FIVE 

BUFFETING CRITERIA. Burnett L. Gadeberg and 
Howard L. Ziff . January 5, 1951. 44p. diagrs., 
photo., tab. (NACA RM A50I27) 



FLIGHT MEASUREMENTS WITH THE DOUGLAS 
D-558-n (BUAERO NO. 37974) RESEARCH AIR- 
PLANE. MEASUREMENTS OF THE DISTRIBUTION 
OF THE AERODYNAMIC LOAD AMONG THE WING, 
FUSELAGE, AND HORIZONTAL TAIL AT MACH 
NUMBERS UP TO 0.87. John P. Mayer and George 
M. Valentine. January 19, 1951. 33p. diagrs., 
photos., tab. (NACA RM L50J13) 



SUMMARY OF SPIN AND RECOVERY CHARACTER- 
ISTICS OF 12 MODELS OF FLYING- WING AND 
UNCONVENTIONAL-TYPE AIRPLANES. Ralph W. 
Stone, Jr., and Burton E, Hultz. March 1, 1951. 
95p. diagrs., photo., tabs. (NACA RM L50L29) 



AN INVESTIGATION OF THE LONGITUDINAL CHAR- 
ACTERISTICS OF THE X-3 CONFIGURATION WITH 
WING AND HORIZONTAL TAIL SURFACES OF 
ASPECT RATIO 3.0 BY MEANS OF ROCKET- 
PROPELLED MODELS. RESULTS AT HIGH LIFT 
COEFFICIENTS. Robert F. Peck and Jesse L. 
Mitchell. August 27, 1951. 34p. diagrs., photos. 
(NACA RM L51G10) 



WIND-TUNNEL TESTS OF A l/12-SCALE MODEL 
OF THE X-3 AIRPLANE AT SUBSONIC AND SUPER- 
SONIC SPEEDS. Robert N. Olson and Robert S. 
Chubb. September 14, 1951. lllp. diagrs., photo., 
tabs. (NACA RM A51F12) 



ANALYSIS OF LONGITUDINAL STABILITY AND 
TRIM OF THE BELL X-l AIRPLANE AT A LIFT 
COEFFICIENT OF 0.3 TO MACH NUMBERS NEAR 
1.05. Hubert M. Drake, John R. Carden, and 
Harry P. Clagett. October 1951. 30p. diagrs., 
photo., tab. (NACA RM L51H01) 



FREE-SPINNING TUNNEL INVESTIGATION OF A 
1/20-SCALE MODEL OF THE DOUGLAS X-3 AIR- 
PLANE. Burton E. Hultz. December 26, 1951. 
23p. diagrs., photos., tab. (NACA RM L51K12) 



HANDLING QUALITIES OF HIGH-SPEED AIRPLANES. 
W. C. Williams and A. S. Crossfield. January 1952. 
I7p. diagrs. (NACA RM L52A08) 



THE STATIC AND DYNAMIC LONGITUDINAL STA- 
BILITY CHARACTERISTICS OF SOME SUPERSONIC 
AIRCRAFT CONFIGURATIONS. Jesse L. Mitchell. 
January 1952. 19p. diagrs. (NACA RM L52A10a) 



120 



(1) AERODYNAMICS 



ANALYTICAL AND EXPERIMENTAL INVESTIGA- 
TION OF INLET -ENGINE MATCHING FOR 
TURBOJET -POWERED AIRCRAFT AT MACH NUM- 
BERS UP TO 2.0. Carl F. Schueller and Fred T, 
Esenwein. February 1952. • 31p. diagrs., photos. 
(NACA RM E51K20) 



WING LOAD DISTRIBUTION ON A SWEPT-WING 
AIRPLANE IN FLIGHT AT MACH NUMBERS UP TO 
1.11 AND COMPARISON WITH THEORY. L. Stewart 
Rolls and Frederick H. Matteson. April 1952. 73p. 
diagrs., photos., tabs. (NACA RM A52A31) 



PERFORMANCE CHARACTERISTICS AT MACH 
NUMBERS TO 2.0 OF VARIOUS TYPES OF SIDE IN- 
LETS MOUNTED ON FUSELAGE OF PROPOSED 
SUPERSONIC AIRPLANE. I - TWO-DIMENSIONAL 
COMPRESSION-RAMP INLETS WITH SEMICIRCU- 
LAR COWLS. Alfred S. Valerino, July 1952. 43p. 
diagrs., photos., tab. (NACA RM E52E02) 



AN INVESTIGATION OF A 0.16-SCALE MODEL OF 
THE DOUGLAS X-3 AIRPLANE. TO DETERMINE 
MEANS OF IMPROVING THE LOW -SPEED LONGI- 
TUDINAL STABILITY AND CONTROL CHARACTER- 
ISTICS. John W. McKee and John M. Riebe. 
November 1952. 90p. diagrs., photos., tabs. 
fNACA RM L52H01) 



SOME MEASUREMENTS OF FLYING QUALITIES OF 
A DOUGLAS D-558-H RESEARCH ADIPLANE DUR- 
ING FLIGHTS TO SUPERSONIC SPEEDS. Herman O. 
Ankenbruck and Theodore E. Dahlen. March 1953. 
25p. diagrs., photos., tab. (NACA RM L53A06)- 



FLIGHT DETERMINATION OF THE LONGITUDINAL 
STABDUTY IN ACCELERATED MANEUVERS AT 
TRANSONIC SPEEDS FOR THE DOUGLAS D-558-H 
RESEARCH AIRPLANE INCLUDING THE EFFECTS 
OF AN OUTBOARD WING FENCE. Jack Fischel and 
Jack Nugent. March 1953. 28p. diagrs., photo., 
tab. (NACA RM L53A16) 



MAXIMUM ALTITUDE AND MAXIMUM MACH NUM- 
BER OBTAINED WITH THE MODIFIED DOUGLAS 
D-558-H RESEARCH AIRPLANE DURING DEMON- 
STRATION FLIGHTS. Theodore E. Dahlen. April 
1953. 14p. diagrs., tabs. (NACA RM L53B24) 



SOME MEASUREMENTS OF THE BUFFET REGION 
OF A SWEPT-WING RESEARCH AIRPLANE DURING 
FLIGHTS TO SUPERSONIC MACH NUMBERS. 
Thomas F. Baker. May 1953. 14p. diagrs., 
photos., tab. (NACA RM L53D06) 



MEASUREMENTS OBTAINED DURING THE GLIDE- 
FLIGHT PROGRAM OF THE BELL X-2 RESEARCH 
AIRPLANE. Richard E. Day. July 30, 1953. 27p. 
diagrs., photos., tabs. (NACA RM L53G03a) 



A ROCKET-MODEL INVESTIGATION OF THE LON- 
GITUDINAL STABILITY, LIFT, AND DRAG CHAR- 
ACTERISTICS OF THE DOUGLAS X-3 CONFIGURA- 
TION WITH HORIZONTAL TAIL OF ASPECT RATIO 
4.33. Robert F. Peck and James A. Hollinger. 
August 1953. 33p. diagrs., photos. 
(NACA RM L53F19a) 



TRANSONIC FLIGHT MEASUREMENT OF THE 
AERODYNAMIC LOAD ON THE EXTENDED SLAT 
OF THE DOUGLAS D- 558-11 RESEARCH AIRPLANE. 
James R. Peele. August 1953. 34p. diagrs., 

photos., tab. (NACA RM L53F29) 



CORRELATION OF FLIGHT AND WIND-TUNNEL 
MEASUREMENTS OF ROLL-OFF IN LOW-SPEED 
STALLS ON A 3 5° SWEPT-WING AIRCRAFT . Seth 
B. Anderson. September 1953. 17p. diagrs., 
photos., tabs. (NACA RM A53G22) 



FLIGHT MEASUREMENTS OF THE HORIZONTAL- 
TAIL LOADS ON A SWEPT-WING FIGHTER AIR- 
PLANE AT TRANSONIC SPEEDS. Me Win Sadoff. 
November 1953. 58p. diagrs., photo., tab. 
(NACA RM A53G10) 



SOME MEASUREMENTS OF BUFFETING ENCOUN- 
TERED BY A DOUGLAS D-558-R RESEARCH AIR- 
PLANE IN THE MACH NUMBER RANGE FROM 0.5 
TO 0.95. Thomas F . Baker . November 1953. 22p. 
diagrs., photos., tabs. (NACA RM L53I17) 



STATIC LONGITUDINAL STABILITY AND CONTROL 
CHARACTERISTICS OF A 1/16-SCALE MODEL OF 
THE DOUGLAS D-558-II RESEARCH AHIPLANE AT 
MACH NUMBERS OF 1.61 AND 2.01. M. Leroy 
Spearman. November 1953. 34p. diagrs., tabs. 
(NACA RM L53I22) 



STATIC LATERAL STABILITY CHARACTERISTICS 
OF A 1/16-SCALE MODEL OF THE DOUGLAS 
D-558-II RESEARCH AIRPLANE AT MACH NUM- 
BERS OF 1.61 AND 2.01. Frederick C. Grant and 
Ross B. Robinson. November 1953. 39p. diagrs., 
photo., tabs. (NACA RM L53I29a) 



DETERMINATION OF LONGITUDINAL STABILITY 
IN SUPERSONIC ACCELERATED MANEUVERS FOR 
THE DOUGLAS D-558-H RESEARCH AIRPLANE. 
Herman O. Ankenbruck. February 1954. 29p. 
diagrs., photos., tab. (NACA RM L53J20) 



MEASURED DATA PERTAINING TO BUFFETING AT 
SUPERSONIC SPEEDS OF THE DOUGLAS D-558-II 
RESEARCH AIRPLANE. Thomas F. Baker. 
February 1954. 16p. diagrs., photos., tab. 
(NACA RM L53L10) 



EFFECT OF WING SLATS AND INBOARD WING 
FENCES ON THE LONGITUDINAL STABILITY 
CHARACTERISTICS OF THE DOUGLAS D-558-H 
RESEARCH AIRPLANE IN ACCELERATED MANEU- 
VERS AT SUBSONIC AND TRANSONIC SPEEDS. 
Jack Fischel. February 1954. 125p. diagrs., 
photos., tabs. (NACA RM L53L16) 



LOW-SPEED CHORDWISE PRESSURE DISTRIBU- 
TIONS NEAR THE MIDSPAN STATION OF THE 
SLOTTED FLAP AND AILERON OF A 1/4 -SCALE 
MODEL OF THE BELL X-l AIRPLANE WITH A 
4 -PERCENT -THICK, ASPECT -RATIO-4, UNSWEPT 
WING. WiUiamC. Moseley, Jr., and Robert T. 
Taylor. March 1954. 59p. diagrs., photos., tabs. 
(NACA RM L53L18) 



LIFT AND DRAG CHARACTERISTICS OF THE 
DOUGLAS D-558-II RESEARCH AIRPLANE OB- 
TAINED IN EXPLORATORY FLIGHTS TO A MACH 
NUMBER OF 2.0. Jack Nugent. August 1954. 20p. 
diagrs., photo., tab. (NACA RM L54F03) 



EFFECTS OF CANOPY, REVISED VERTICAL TAIL, 
AND A YAW-DAMPER VANE ON THE AERODYNAM- 
IC CHARACTERISTICS OF A 1/16-SCALE MODEL 
OF THE DOUGLAS D-558-H RESEARCH AIRPLANE 
AT A MACH NUMBER OF 2.01. Ross B. Robinson. 
August 1954. 29p. diagrs., tabs. 
(NACA RM L54F25) 



( 1 ) AERODYNAMICS 



121 



WING PRESSURE DISTRIBUTIONS AT LOW LIFT 
FOR THE XF-92A DELTA-WING AIRPLANE AT 
TRANSONIC SPEEDS. Earl R. Keener. October 
1954. 54p. diagrs., photos., tabs. 
(NACA RM H54H06) 



LONGITUDINAL STABILITY CHARACTERISTICS IN- 
ACCELERATED MANEUVERS AT SUBSONIC AND 
TRANSONIC SPEEDS OF THE DOUGLAS D-558-II 
RESEARCH AIRPLANE EQUIPPED WITH A 
LEADING-EDGE WING CHORD-EXTENSION. Jack 
Fischel and Cyril D. Brunn. October 1954. 62p. 
diagrs., photos., tab. (NACA RM H54H16) 



THE EFFECT OF AN OPERATING PROPELLER ON 
THE AERODYNAMIC CHARACTERISTICS AT HIGH 
SUBSONIC SPEEDS OF A MODEL OF A VERTICAL- 
RISING AIRPLANE HAVING AN UNSWEPT WING OF 
ASPECT RATIO 3. Fred B. Sutton and Donald A. 
Buell. November 1954. 90p. diagrs., photos., 
tabs. (NACA RM A52E06) 



DETERMINATION OF LONGITUDINAL HANDLING 
QUALITIES OF THE D-558-II RESEARCH AIRPLANE 
AT TRANSONIC AND SUPERSONIC SPEEDS TO A 
MACH NUMBER OF ABOUT 2.0. Herman O 
Ankenbruck. November 1954. 25p. diagrs., photos., 
tab. (NACA RM H54G29a) 



LIFT AND DRAG CHARACTERISTICS OF THE 
DOUGLAS X-3 RESEARCH AIRPLANE OBTAINED 
DURING DEMONSTRATION FLIGHTS TO A MACH 
NUMBER OF 1.20. Donald R. Bellman and 
Edward D. Murphy. December 1954. 23p. diagrs., 
photos., tab. (NACA RM H54I17) 



LATERAL MOTIONS ENCOUNTERED WITH THE 
DOUGLAS D-558-II ALL-ROCKET RESEARCH AIR- 
PLANE DURING EXPLORATORY FLIGHTS TO A 
MACH NUMBER OF 2.0. Herman O. Ankenbruck 
and Chester H. Wolowicz. December 1954. 32p. 
diagrs., photos., tab. (NACA RM H54I27) 



ROLLING PERFORMANCE OF THE REPUBLIC 
YF-84F AIRPLANE AS MEASURED IN FLIGHT. 
John B. McKay. January 1955. 2 4p. diagrs., 
photo . , tab . (NACA RM H 54G20a) 



A LIMITED FLIGHT INVESTIGATION OF THE 
EFFECT OF DYNAMIC VIBRATION ABSORBERS 
ON THE RESPONSE OF AN AIRPLANE STRUCTURE 
DURING BUFFETING. Jim Rogers Thompson and 
John E. Yeates, Jr. January 1955. 29p. diagrs., 
photos. (NACA RM L54K02) 



RESULTS OF MEASUREMENTS MADE DURING 
THE APPROACH AND LANDING OF SEVEN HIGH- 
SPEED RESEARCH AIRPLANES. Wendell H. 
Stillwell. February 1955. 25p. diagrs., tab. 
(NACA RM H54K24) 



INVESTIGATION OF THE LATERAL STABILITY 
CHARACTERISTICS OF THE DOUGLAS X-3 CON- 
FIGURATION AT MACH NUMBERS FROM 0.6 TO 
1.1 BY MEANS OF A ROCKET -PROPELLED 
MODEL. Jesse L. Mitchell and Robert F. Peck. 
February 1955. 37p. diagrs., photo., tabs. 
(NACA RM L54L20) 



WING-LOAD MEASUREMENTS AT SUPERSONIC 
SPEEDS OF THE DOUGLAS D-558-II RESEARCH 
AIRPLANE. Glenn H. Robinson, George E. Cothren, 
Jr., and Chris Pembo. March 1955. 20p. diagrs., 
photos., tab. (NACA RM H54L27) 



PRELIMINARY FLIGHT -DETERMINED PRESSURE 
DISTRIBUTIONS OVER THE WING OF THE 
DOUGLAS X-3 RESEARCH AIRPLANE AT SUBSONIC 
AND TRANSONIC MACH NUMBERS. Gareth H. 
Jordan and C. Kenneth Hutchins, Jr. April 1955. 
34p. diagrs., photos., tabs. (NACA RM H55A10) 



LATERAL STABILITY CHARACTERISTICS AT LOW 
LIFT BETWEEN MACH NUMBERS OF 0.85 AND 1.15 
OF A ROCKET-PROPELLED MODEL OF A SUPER- 
SONIC AIRPLANE CONFIGURATION HAVING A 
TAPERED WING WITH CIRCULAR-ARC SECTIONS 
AND 40° SWEEPBACK. Charles T. D'Aiutolo and 
Allen B. Henning. April 1955. 50p. diagrs., 
photos., tabs. (NACA RM L55A31) 



LATERAL STABILITY AND CONTROL CHARACTER- 
ISTICS OF THE CONVAIR XF-92A DELTA-WING 
AIRPLANE AS MEASURED IN FLIGHT. Thomas R. 
Slsk and Duane O. Muhleman. May 1955. 55p. 
diagrs., photos., tabs. (NACA RM H55A17) 



STUDY OF SOME EFFECTS OF STRUCTURAL 
FLEXIBILITY ON THE LONGITUDINAL MOTIONS 
AND LOADS AS OBTAINED FROM FLIGHT MEAS- 
UREMENTS OF A SWEPT -WING BOMBER. James 
J. Donegan and Carl R. Huss. May 1955. 53p. 
diagrs., tabs. (NACA RM L54L16) 



PRELIMINARY RESULTS FROM FLIGHT MEASURE- 
MENTS IN GRADUAL-TURN MANEUVERS OF THE 
WING LOADS AND THE DISTRIBUTION OF LOAD 
AMONG THE COMPONENTS OF A BOEING B-47A 
AIRPLANE. T. V. Cooney, William H. Andrews, 
and William A. McGowan. June 1955. 20p. diagrs., 
photo., tab. (NACA RM L55B02) 



STABILITY AND CONTROL CHARACTERISTICS 
OBTAINED DURING DEMONSTRATION OF THE 
DOUGLAS X-3 RESEARCH AIRPLANE. Richard E. 
Day and Jack Fischel. July 1955. 51p. diaers., 
photos., tab. (NACA RM H55E16) 



EFFECT OF SEVERAL WING MODIFICATIONS ON 
THE LOW-SPEED STALLING CHARACTERISTICS OF 
THE DOUGLAS D-558-II RESEARCH AIRPLANE. 
Jack Fischel and Donald Reisert. July 1956. 62p. 
diagrs., photos., tabs. (NACA RM H55E31a) 



INVESTIGATION AT HIGH SUBSONIC SPEEDS OF 
THE EFFECTS OF VARIOUS UNDERWING 
EXTERNAL-STORE ARRANGEMENTS ON THE 
AERODYNAMIC CHARACTERISTICS OF A 1/16- 
SCALE MODEL OF THE DOUGLAS D- 558-0 
RESEARCH A DIP LANE. H. Norman Silvers and 
Thomas J. King, Jr. July 1955. 59p. diagrs., 
photos., tab. (NACA RM L55D11) 



FLIGHT MEASUREMENTS OF THE LATERAL 
RESPONSE CHARACTERISTICS OF THE CONVAUt 
XF-92A DELTA-WING AIRPLANE. Euclid C. 
Holleman. August 1955. 37p. diagrs., tabs. 
(NACA RM H55E26) 



A FLIGHT INVESTIGATION OF THE HANDLING 
CHARACTERISTICS OF A FIGHTER AIRPLANE 
CONTROLLED THROUGH AUTOMATIC-PILOT 
CONTROL SYSTEMS. S. A. Sjoberg. September 
1955. 12p. diagrs., tabs. (NACA RM L55F01b) 



AERODYNAMIC CHARACTERISTICS AT MACH NUM- 
BERS FROM 0.7 TO 1.75 OF A FOUR-ENGINE 
SWEPT -WING AIRPLANE CONFIGURATION AS 
OBTAINED FROM A ROCKET -PROPELLED MODEL 
TEST. Rowe Chapman, Jr. September 1955. 39p. 
diagrs., photos., tabs. (NACA RM L55F23) 



122 



(1) AERODYNAMICS 



FLIGHT MEASUREMENTS OF DIRECTIONAL STA- 
BILITY TO A MACH NUMBER OF 1.48 FOR AN 
AIRPLANE TESTED WITH THREE DIFFERENT 
VERTICAL TAIL CONFIGURATIONS. Hubert M. 
Drake, Thomas W. Finch, and James R. PeelP, 
October 1955. 22p. diagrs., photos,, tab. 
(NACA RM H55G26) 



WING PRESSURE DISTRIBUTIONS OVER THE LIFT 
RANGE OF THE CONVAIR XF-92A DELTA-WING 
AIRPLANE AT SUBSONIC AND TRANSONIC 
SPEEDS, Earl R. Keener and Gareth H. Jordan. 
November 1955. 135p. diagrs., photos., tabs. 
(NACA RM H55G07) 



WIND-TUNNEL MEASUREMENTS OF THE DYNAMIC 



CROSS DERIVATIVE C 



Wc 



(ROLLING MO- 



MENT DUE TO YAWING VELOCITY AND TO AC- 
CELERATION IN SIDESLIP) OF THE DOUGLAS 
D-558-II AIRPLANE AND ITS COMPONENTS AT 
SUPERSONIC SPEEDS INCLUDING DESCRIPTION 
OF THE TECHNIQUE. William B. Boatright. 
November 1955. 57p. diagrs., photos. 
(NACARML55H16) 



TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF EXTERNAL STORES AND STORE 
POSITION ON THE AERODYNAMIC CHARACTERIS- 
TICS OF A 1/16-SCALE MODEL OF THE DOUGLAS 
D-558-U RESEARCH AIRPLANE. Thomas C. Kelly. 
November 1955. 31p. diagrs., photos., tab. 
(NACA RM L55I07) 



EFFECT OF LARGE NEGATIVE DIHEDRAL OF THE 
HORIZONTAL TAIL ON LONGITUDINAL. AND LAT- 
ERAL STABILITY CHARACTERISTICS OF A 
SWEPT-WING CONFIGURATION AT TRANSONIC 
SPEEDS. Donald D. Arabian. January 1956. 24p. 
diagrs., photos. (NACA RM L55I20) 



MACH NUMBER MEASUREMENTS AND CALD3RA- 
TIONS DURING FLIGHT AT HIGH SPEEDS AND AT 
HIGH ALTITUDES INCLUDING DATA FOR THE 
D-558-n RESEARCH AIRPLANE. Cyril D. Brunn 
and Wendell H. Stillwell. March 1956. 31p. diagrs., 
tabs. (NACA RM H55J18) 



FLIGHT MEASUREMENTS OF HORIZONTAL -TAIL 
LOADS ON THE DOUGLAS X-3 RESEARCH AIR- 
PLANE. Harriet J. Stephenson. April 1956. 33p. 
diagrs., photo., tab. (NACA RM H56A23) 



A FLIGHT INVESTIGATION OF THE HANDLING 
CHARACTERISTICS OF A FIGHTER AIRPLANE 
CONTROLLED THROUGH AN ATTITUDE TYPE OF 
AUTOMATIC PILOT. S. A. Sjoberg, Walter R. 
Russ*U, and William L. Alford. April 1956. 60p. 
diagrs., photos., tabs- (NACA RM L56A12) 



EFFECT OF FUSELAGE AIR BRAKES ON THE 
LONGITUDINAL STABILITY CHARACTERISTICS OF 
A SWEPT-WING FIGHTER MODEL AT TRANSONIC 
SPEEDS. Donald D. Arabian. April 1956. 22p. 
diagrs., photos. (NACA RM L 56 A 25a) 



SOME NOTES ON THE VIOLENT LATERAL - 
LONGITUDINAL COUPLING MOTIONS OF THE 
DOUGLAS X-3 AIRPLANE IN AILERON ROLLS. 
Ra)pa W. Stone, Jr. May 1956. 35p. diagrs., tab. 
(NACA RM L5«C15) 



EFFECT OF SEVERAL WING MODIFICATIONS ON 
THE SUBSONIC AND TRANSONIC LONGITUDINAL 
HANDLING QUALITIES OF THE DOUGLAS D-558-II 
RESEARCH AIRPLANE. Jack Fischel and Donald 
Reisert. June 1956. 57p. diagrs., photos., tabs. 
(NACA RM H56C30) 



EFFECT OF WING SIZE AND AMOUNT OF INDEN- 
TATION ON APPLIC ABILITY OF TRANSONIC AREA 
RULE TO SWEPT-WING CONFIGURATIONS. 
James Rudyard Hall. July 1956. 33p. diagrs., 
photos., tabs. (NACA RM L55F03) 



WIND-TUNNEL INVESTIGATION AT HIGH SUBSONIC 
SPEEDS OF JET, SPOILER, AND AILERON CON- 
TROLS ON A 1/16-SCALE MODEL OF THE DOUGLAS 
D-558-H RESEARCH AIRPLANE . Raymond D . 
Vogler. July 1956. 52p. diagrs., photo., tabs. 
(NACA RM L56E25) 



STATISTICAL MEASUREMENTS OF LANDING CON- 
TACT CONDITIONS OF FIVE MILITARY AIRPLANES 
DURING ROUTINE DAYTIME OPERATIONS. 
Norman S. Silsby. August 1956. 17p. diagrs., tabs. 
(NACA RM L56F21a) 



A SEMIEMPIRICAL PROCEDURE FOR ESTIMATING ' 
WING BUFFET LOADS IN THE TRANSONIC REGION. 
T. H. Skopinski and Wilber B. Huston. September 
1S56. 22p. diagrs., tab. (NACA RM L56E01) 



WIND-TUNNEL INVESTIGATION OF THE DAMPING 
IN ROLL OF THE DOUGLAS D-558-H RESEARCH 
AIRPLANE AND ITS COMPONENTS AT SUPERSONIC 
SPEEDS. Russell W. McDearmon. September 1956. 
36p. diagrs., photos. (NACA RM L56F07) 



WTND-TUNNEL MEASUREMENTS OF WING BUF- 
FETING ON 1/16-SCALE MODEL OF DOUGLAS 
D-558-D RESEARCH AIRPLANE. William B. Kemp, 
Jr., and Thomas J. King, Jr. September 1956. 
34p. diagrs., photos., tabs. (NACA RM L56G31) 



WING LOADS AND LOAD DISTRIBUTIONS THROUGH- 
OUT THE LIFT RANGE OF THE DOUGLAS X-3 
RESEARCH ADIPLANE AT TRANSONIC SPEEDS. 
Earl R. Keener and Gareth H. Jordan. November 
1956. 191p. diagrs., photo., tabs. 
(NACARMH56G13) 



ANALYSIS OF THE VERTICAL-TAIL LOADS MEAS- 
URED DURING A FLIGHT INVESTIGATION AT 
TRANSONIC SPEEDS OF THE DOUGLAS X-3 RE- 
SEARCH AIRPLANE. William L. Marcy, Harriet J . 
Stephenson, and Thomas V. Cooney. November 1956. 
32p. diagrs., photo., tab. (NACA RM H56H08) 



LIFT -CURVE SLOPES DETERMINED IN FLIGHT ON 
A FLEXIBLE SWEPT-WING JET BOMBER. William 
S. Aiken, Jr M and Raymond A. Fisher. December 
1956. 49p. diagrs., photos., tabs. 
(NACARM L56E21a) 



HORIZONTAL-TAIL PARAMETERS AS DETER- 
MINED FROM FLIGHT-TEST TAIL LOADS ON A 
FLEXIBLE SWEPT-WING JET BOMBER. William 
S. Aiken, Jr., and Raymond A. Fisher. January 
1957. 42p. diagrs., photos., tabs. 
(NACA RM L56J02) 



AN ANALOG COMPUTER STUDY v¥ SEVERAL STA- 
BILITY AUGMENTATION SCHEMES DESIGNED TO 
ALLEVIATE ROLL-INDUCED INSTABILITY. Brent 
Y. Creer. February 1657. 50p. diagrs., tab. 
(NACA RM A56H30) 



AN ANALYSIS OF VERTICAL-TAIL LOADS MEAS- 
URED IN FLIGHT ON A SWEPT-WING BOMBER 
AIRPLANE. WilUam A. McGowan and T- V. 
Cooney. May 1957. 53p. diagrs., photo., tabs. 
(NACA RM L57B19) 



123 



( 1 ) AERODYNAMICS 



FLIGHT DATA PERTINENT TO BUFFETING AND 
MAXIMUM NORMAL-FORCE COEFFICIENT OF THE 
DOUGLAS X-3 RESEARCH AIRPLANE. Thomas F. 
Baker, James A. Martin, and Betty J. Scott, 
November 1957. 41p. diagrs., photo., tabs. 
(NACA RM H57H09) 



FLIGHT INVESTIGATION OF THE TRANSONIC 
LONGITUDINAL AND LATERAL HANDLING QUAL- 
ITIES OF THE DOUGLAS X-3 RESEARCH AIRPLANE. 
Jack Fischel, Euclid C. Holleman, and Robert A. 
Tremant. December 1957. 61p. diagrs., photos., 
tab. (NACA RM H 57105) 



ANALYSIS OF HORIZONTAL -TAIL LOADS IN 
PITCHING MANEUVERS ON A FLEXIBLE SWEPT- 
WING JET BOMBER. William S. Aiken, Jr. 
December 1957. 58p. diagrs., photo., tabs. 
(NACA TN 4191) 



HIGH-SPEED LANDING LOADS MEASURED ON THE 
DOUGLAS X-3 RESEARCH AIRPLANE. William L. 
Marcy. February 1958. 24p. diagrs., photo., tabs. 
(NACA RM H57L06) 



PRELIMINARY FLIGHT SURVEY OF FUSELAGE 
AND BOUNDARY -LAYER SOUND- PRESSURE 
LEVELS. Norman J. McLeod and Gareth H. Jordan. 

May 1958. 25p. diagrs., photos. 
(NACA RM H58B11) 



AN EVALUATION OF EFFECTS OF FLEXIBILITY 
ON WING STRAINS IN ROUGH AIR FOR A LARGE 
SWEPT-WING AIRPLANE BY MEANS OF EXPERI- 
MENTALLY DETERMINED FREQUENCY -RESPONSE 
FUNCTIONS WITH AN ASSESSMENT OF RAN DOM - 
PROCESS TECHNIQUES EMPLOYED. Thomas L. 
Coleman, Harry Press, and May T. Meadows. July 
3958. ii, 74p. diagrs., pboto., tabs. 
(NACA TN 4291) 



WIND-TUNNEL INVESTIGATION OF THE AERO- 
DYNAMIC AND STRUCTURAL DEFLECTION CHAR- 
ACTERISTICS OF THE GOODYEAR INFLATOPLANE. 
Bennie W. Cocke, Jr. September 1958. 56p. 
diagrs., photos. (NACA RM L58E09) 



(1.7.1.3) 
PERFORMANCE 



ESTIMATED TRANSONIC FLYING QUALITIES OF A 
TAILLESS AIRPLANE BASED ON A MODEL INVES- 
TIGATION. Charles J. Donlan and Richard E. Kuhn. 
June 8, 1949. 63p. diagrs., photos., tabs. 
(NACA RM L9D08) 



LOITERING AND RANGE PERFORMANCE OF 
TURBOJET-POWERED AIRCRAFT DETERMINED 
BY OFF -DESIGN ENGINE CYCLE ANALYSIS. 
Stanley L. Koutz and Reece V. Hensley. 
February 1952. 45p. diagrs., tab. 
(NACA RM E51K29) 



AN ANALYSIS OF THE EFFECT OF A CURVED 
RAMP ON THE TAKE-OFF PERFORMANCE OF 
CATAPULT-LAUNCHED AIRPLANES. Wilmer H. 
Reed, III. November 1952. 28p. diagrs., tab. 
(NACA RM L52I05) 



MAXIMUM ALTITUDE AND MAXIMUM MACH NUM- 
BER OBTAINED WITH THE MODIFIED DOUGLAS 
D-558-H RESEARCH AIRPLANE DURING DEMON- 
STRATION FLIGHTS. Theodore E. Dahlen. April 
1953. 14p. diagrs., tabs. (NACA RM L53B24) 



LIFT AND DRAG CHARACTERISTICS OF THE 
DOUGLAS D- 5 58 -II RESEARCH AIRPLANE OB- 
TAINED IN EXPLORATORY FLIGHTS TO A MACH 
NUMBER OF 2.0. Jack Nugent. August 1954. 20p. 
diagrs., photo., tab. (NACA RM L54F03) 



LIFT AND DRAG CHARACTERISTICS OF THE 
DOUGLAS X-3 RESEARCH AIRPLANE OBTAINED 
DURING DEMONSTRATION FLIGHTS TO A MACH 
NUMBER OF 1.20. Donald R. Bellman and 
Edward D, Murphy. December 1954. 23p. diagrs., 
photos., tab. (NACA RM H54I17) 



A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
STORE AND HORIZONTAL-TAIL LOADS AND SOME 
EFFECTS OF FUSELAGE-AFTERBODY MODIFICA- 
TIONS ON A SWEPT-WING FIGHTER AIRPLANE. 
Joseph M. HaUissy, Jr., and Louis Kudlacik. April 
1956. 79p. diagrs., photos. (NACA RM L56A26) 



MINIMUM WAVE DRAG FOR ARBITRARY ARRANGE- 
MENTS OF WINGS AND BODIES. Robert T. Jones. 
1957. ii, 6p. diagrs., photo. (NACA Rept. 1335. 
Supersedes TN 3530) 



A COMPARATIVE ANALYSIS OF THE PERFORM- 
ANCE OF LONG-RANGE HYPERVELOCITY 
VEHICLES. Alfred J. Eggers, Jr., H. Julian Allen, 
and Stanford E. Neice. October 1957. (i), 66p. 
diagrs. (NACA TN 4046. Supersedes RM A54L10) 



INVESTIGATION OF THE EFFECTS OF PRO- 
PELLER DIAMETER ON THE ABILITY OF A 
FLAPPED WING, WITH AND WITHOUT 
BOUNDARY- LAYER CONTROL, TO DEFLECT A 
PROPELLER SLIPSTREAM DOWNWARD FOR 
VERTICAL TAKE-OFF. Kenneth P. Spreemann. 
December 1957. 47p. diagrs., photos. 
(NACA TN 4181) 



EXPERIMENTAL INVESTIGATION OF THE 
LATERAL TRIM OF A WING-PROPELLER COM- 
BINATION AT ANGLES OF ATTACK UP TO 90° 
WITH ALL PROPELLERS TURNING IN THE SAME 
DIRECTION. William A. Newsom, Jr. January 
1958. 27p. diagrs. (NACA TN 4190) 



EFFECTIVENESS OF BOUNDARY- LAYER CON- 
TROL, OBTAINED BY BLOWING OVER A PLAIN 
REAR FLAP IN COMBINATION WITH A FORWARD 
SLOTTED FLAP, IN DEFLECTING A SLIPSTREAM 
DOWNWARD FOR VERTICAL TAKE-OFF. 
Kenneth P. Spreemann. February 1958. 32p. 
diagrs., photo. (NACA TN 4200) 



WIND-TUNNEL INVESTIGATION OF THE HIGH- 
SUBSONIC STATIC LONGITUDINAL STABILITY 
CHARACTERISTICS OF SEVERAL WING-BODY CON- 
FIGURATIONS DESIGNED FOR HIGH LIFT-DRAG 
RATIOS AT A MACH NUMBER OF 1.4. Paul G. 
Fournier, July 1958. 42p. diagrs., photo., tab. 
(NACA TN 4340) 



EFFECTS OF PROPELLER POSITION AND OVER- 
LAP ON THE SLIPSTREAM DEFLECTION CHAR- 
ACTERISTICS OF A WING-PROPELLER CONFIG- 
URATION EQUIPPED WITH A SLIDING AND 
FOWLER FLAP. William C. Hayes, Jr., Richard E. 
Kuhn, and Irving R. Sherman. September 1958. 
81p. diagrs., photos. (NACA TN 4404) 



124 



(1) AERODYNAMICS 



(1.7.2) 
MISSILES 



EFFECT OF FUEL DENSITY AND HEATING VALUE 
ON RAM -JET AIRPLANE RANGE. Hugh M. 
Henneberry. February 1952. 56p. diagrs., tabs. 
(NACARM E51L21) 



AERODYNAMICS OF SLENDER BODIES AT MACH 
NUMBER OF 3.12 AND REYNOLDS NUMBERS 
FROM 2 x 106 TO 15 x 106. II - AERODYNAMIC 
LOAD DISTRIBUTIONS OF SERIES OF FIVE BODIES 
HAVING CONICAL NOSES AND CYLINDRICAL 
AFTERBODIES. John R. Jack and Lawrence I. 
Gould. May 1952, 28p. diagrs., photos., tabs. 
(NACA RM E52C10} 



A PRESSURE -DISTRIBUTION INVESTIGATION OF A 
FINENESS-RATIO-12.2 PARABOLIC BODY OF REV- 
OLUTION (NACA RM-10) AT M = 1.59 AND 
ANGLES OF ATTACK UP TO 36°. Morton Cooper, 
John P. Gapcynski, and Lowell E. Hasel. October 
1952. 89p. diagrs., photos., tabs. 
(NACA RM L52G14a) 



EXPLORATORY ROCKET FLIGHT TESTS TO IN- 
VESTIGATE THE USE OF A FREELY SPINNING 
MONOPLANE TAIL FOR STABILIZING A BODY. 
Paul E. Purser and Joseph E. Stevens. October 
1952. 25p. diagrs., photos., tab. 
(NACA RM L52I05a) 



THEORETICAL INVESTIGATION OF THE PER- 
FORMANCE OF PROPORTIONAL NAVIGATION 
GUIDANCE SYSTEMS - EFFECT OF MISSILE CON- 
FIGURATION ON THE SPEED OF RESPONSE . 
Marvin Abramovltz. January 1953. 20p. diagrs., 
tabs. (NACA RM A52J22) 



AERODYNAMIC CHARACTERISTICS OF TWO FLAT- 
BOTTOMED BODIES AT MACH NUMBER OF 3.12. 
John R. Jack and Barry Moskowitz. April 1954. 
9p. diagrs. (NACA RM E53Lllb) 



DRAG DATA FOR 16-INCH-DIAMETER RAM -JET 
ENGINE WITH DOUBLE -CONE INLET IN FREE 
FLIGHT AT MACH NUMBERS FROM 0.7 TO 1.8. 
Merle L. Jones, Leonard Rabb, and Scott H. 
Simpkinson. October 1954. 52p. diagrs., photos. 
(NACA RM E54H02> 



APPLICATION OF STATISTICAL THEORY TO 
BEAM-RIDER GUIDANCE IN THE PRESENCE OF 
NOISE . I - WIENER FILTER THEORY . E Iwood C . 
Stewart. August 1955. 40p. diagrs., tabs. 
(NACARM A55E 11) 



ANALYSIS OF A FLIGHT INVESTIGATION AT 
SUPERSONIC SPEEDS OF A SIMPLE HOMING 
SYSTEM. Robert A. Gardiner, Clarence L. Gillis, 
andG. B. Graves, Jr. January 1956. 55p. diagrs., 
photos. (NACA RM L55J28) 



A COMPARATIVE ANALYSIS OF THE PERFORM- 
ANCE OF LONG-RANGE HYPERVELOCITY 
VEHICLES. Alfred J. Eggers, Jr., H. Julian Allen, 
and Stanford E. Neice. October 1957. (i), 66p. 
diagrs. (NACA TN 4046. Supersedes RM A54L10) 



MOTION OF A BALLISTIC MISSILE ANGULARLY 
MISALINED WITH THE FLIGHT PATH UPON EN- 
TERING THE ATMOSPHERE AND ITS EFFECT UP- 
ON AERODYNAMIC HEATING, AERODYNAMIC 
LOADS, AND MISS DISTANCE. H. Julian Allen. 
October 1957. 66p. diagrs., tabs. (NACA TN 4048. 
Supersedes RM A56F15) 



DEVELOPMENT OF A PISTON-COMPRESSOR TYPE 
LIGHT-GAS GUN FOR THE LAUNCHING OF FREE- 
FLIGHT MODELS AT HIGH VELOCITY . A . C . 
Charters, B. PatDenardo, and Vernon J. Rossow. 
November 1957. (1), 95p. diagrs., photos., tabs. 
(NACA TN 4143. Supersedes RM A55G11) 



THREE-DEGREE-OF-FREEDOM EVALUATION 
OF THE LONGITUDINAL TRANSFER FUNCTIONS 
OF A SUPERSONIC CANARD MISSILE CONFIGU- 
RATION INCLUDING CHANGES IN FORWARD 
SPEED. Ernest C. Seaberg. December 1957. 
29p. diagrs., photo., tabs. (NACA TN 4192. 
Supersedes RM L54C02) 

SUMMARY OF FLUTTER EXPERIENCES AS A 
GUIDE TO THE PRELIMINARY DESIGN OF LIFTING 
SURFACES ON MISSILES. Dennis J. Martin. 
February 1958. 21p. diagrs. (NACA TN 4197. 
Supersedes RM L51J30) 



AN ANALYSIS OF THE OPTIMIZATION OF A BEAM 
RIDER MISSILE SYSTEM. Marvin Shinbrot and 
Grace C. Carpenter. March 1958. 34p. diagrs. 
(NACA TN 4145) 



APPLICATION OF STATISTICAL THEORY TO 
BEAM-RIDER GUIDANCE IN THE PRESENCE OF 
NOISE. II - MODIFIED WIENER FILTER THEORY. 
Elwood C. Stewart. June 1958. (i), 48p. diagrs., 
tabs. (NACA TN 4278. Supersedes RM A55Ella) 



COMPATIBILITY OF METALS WITH LIQUID FLUO- 
RINE AT HIGH PRESSURES AND FLOW VELOCITIES. 
Harold W. Schmidt. July 1958. 15p. diagrs., 
photo., tab. (NACA RM E58D11) 



DYNAMIC STABILITY OF VEHICLES TRAVERSING 
ASCENDING OR DESCENDING PATHS THROUGH 
THE ATMOSPHERE. Murray Tobak and H. Julian 
Allen. July 1958. (i), 35p. diagrs. 
(NACA TN 4275) 



AN ESTIMATE OF THE FLUCTUATING SURFACE 
PRESSURES ENCOUNTERED IN THE REENTRY OF 
A BALLISTIC MISSILE. Edmund E. Callaghan. 
July 1958. lRp. diagrs. (NACA TN 4315) 



TRANSIENT TEMPERATURE DISTRIBUTION IN A 
TWO-COMPONENT SEMI-INFINITE COMPOSIT E 
SLAB OF ARBITRARY MATERIALS SUBJECTED TO 
AERODYNAMIC HEATING WITH A DISCONTINUOUS 
CHANGE IN EQUILIBRIUM TEMPERATURE Or 
HEAT -TRANSFER COEFFICIENT. Robert L. 
Tr impi and Robert A. Jones. September 1958. 83p. 
diagrs., tabs. (NACA TN 4308) 



AN APPROACH TO THE PROBLEM OF ESTIMATING 
SEVERE AND REPEATED GUST LOADS FOR MIS-, 
SILE OPERATIONS. Harry Press and Roy Steiner. 
September 1958. 44p. diagrs., tab. (NACA TN 4332) 



RELATIVE MOTION IN THE TERMINAL PHASE OF 
INTERCEPTION OF A SATELLITE OR A BALLISTIC 
MISSILE. Richard A. Hord. September 1,958. 33p. 
diagrs., tab. (NACA TN 4399) 



(1.7.2.1) 
COMPONENTS IN COMBINATION 



LARGE-SCALE FLIGHT MEASUREMENTS OF 
ZERO-LIFT DRAG AT MACH NUMBERS FROM 0.90 
TO 1 .95 OF AN ARROW WING IN COMBINATION 
WITH A SMALL BODY. Warren Gillespie, Jr., and 
Richard G. Arbic. January 12, 1951. 17p. diagrs., 
photos., tab. (NACA RM L50K28a) 



125 



(1) AERODYNAMICS 



A COMPARISON OF THE CALCULATED MAXIMUM 
MANEUVER-RESPONSE CHARACTERISTICS OF 
THREE AIR-TO-AIR, BEAM -RIDER, GUIDED MIS- 
SILES HAVING DIFFERENT LIFT RATIOS. Howard 
F. Matthews and ElwoodC. Stewart. September 
1951. 57p. diagrs., tabs. (NACA RM A51F18) 



TESTS AT MACH NUMBER 1.62 OF A SERIES OF 
MISSILE CONFIGURATIONS HAVING TANDEM 
CRUCIFORM LIFTING SURFACES. Carl E . 
Grigsby. January 1952. 106p. diagrs., tabs. 
(NACARM L51J15) 



SPREADING OF EXHAUST JET FROM 16-INCH RAM 
JET AT MACH NUMBER 2.0. Fred Wilcox and 
Donald Pennington. August 1952. 14p. diagrs., 
photo., tab. (NACA RM E52F25) 



PERFORMANCE CHARACTERISTICS OF CANARD- 
TYPE MISSILE WITH VERTICALLY MOUNTED 
NACELLE ENGINES AT MACH NUMBERS 1.5 TO 
2.0. Leonard J. Obery and Howard S. Krasnow. 
September 1952. 25p. diagrs. (NACA RM E52H08) 



INFLUENCE OF FUSELAGE -MOUNTED ROCKET- 
BOOSTERS ON FLOW FIELD AT INLET AND ON 
DIFFUSER PERFORMANCE OF STRUT-MOUNTED 
ENGINE AT MACH NUMBERS OF l.B AND 2.0. 
George A. Wise and Leonard J. Obery. October 
1952. 16p. diagrs. , photos. (NACA RM E 5 2102) 



PERFORMANCE CHARACTERISTICS OF CANARD- 
TYPE MISSILE WITH WING-MOUNTED NACELLE 
ENGINES AT MACH NUMBERS 1 .5 TO 2.0 . Emil J . 
Kremzler and Joseph Davids. November 1952. 
30p. diagrs., tab. (NACA RM E52J08) 



TOTAL-PRESSURE AND SCHLIEREN STUDIES OF 
THE WAKES OF VARIOUS CANARD CONTROL SUR- 
FACES MOUNTED ON A MISSILE BODY AT A MACH 
NUMBER OF 1.93. William B. Boatrlght. 
November 1952. 47p. photos., diagrs. 
(NACA RM L52I29) 



LARGE-SCALE FLIGHT MEASUREMENTS OF 
ZERO-LIFT DRAG OF 10 WING-BODY CONFIGURA- 
TIONS AT MACH NUMBERS FROM 0.8 TO 1.6. 
John D. Morrow and Robert L. Nelson. 
1953. 53p. diagrs., photo., tabs. 
(NACA RM L 5 2D 18a) 



FLIGHT INVESTIGATION OF THE ZERO-LIFT 
DRAG OF TWO RAM -JET MISSILE CONFIGURA- 
TIONS AT MACH NUMBERS FROM 1.00 TO 1.89. 
Clarence A. Brown, Jr., and Walter E. Bressette. 
March 1953. 24p. diagrs., photos. 
(NACA RM L52J24a) 



SOME APPROXIMATE METHODS FOR ESTIMATING 
THE EFFECTS OF AEROELASTIC BENDING OF 
ROCKET -PROPELLED MODEL-BOOSTER COMBI- 
NATIONS. Richard G. Arbic, George White, and 
Warren Gillespie, Jr. March 1953. 40p, diagrs., 
photos., tabs. (NACA RM L53A08) 



WIND-TUNNEL INVESTIGATION OF A RAM -JET 
MISSILE MODEL HAVING A WING AND CANARD 
SURFACES OF DELTA PLAN FORM WITH 70° 
SWEPT LEADING EDGES. FORCE AND MOMENT 
CHARACTERISTICS OF VARIOUS COMBINATIONS 
OF COMPONENTS AT A MACH NUMBER OF 1.6. 
Clyde V. Hamilton, Cornelius Driver, and John R. 
Sevier, Jr. March 1953. 48p. diagrs., photo., 
tabs. (NACA RM L53A14) 



INVESTIGATION OF THE DRAG OF BLUNT -NOSED 
BODIES OF REVOLUTION IN FREE FLIGHT AT 
MACH NUMBERS FROM 0.6 TO 2.3. Harvey A. 
Wallskog and Roger G. Hart. June 1953. 28p. 
diagrs., photos., tab. (NACA RM L53D14a) 



THEORETICAL CALCULATIONS OF THE STABILI- 
TY DERIVATIVES AT SUPERSONIC SPEEDS FOR A 
HIGH-SPEED AIRPLANE CONFIGURATION. 
Kenneth Margolis and Percy J. Bobbitt. October 
1953. 59p. diagrs., tab. (NACA RM L53G17) 



A METHOD FOR ESTIMATING THE ROLLING MO- 
MENTS CAUSED BY WING-TAIL INTERFERENCE 
FOR MISSILE AT SUPERSONIC SPEEDS. Sherman 
Edwards and Katsumi Htkk-j. November 1953. 68p. 
diagrs., tabs. (NACA RM A53H18) 



AN ANALYSIS OF PRESSURE toi JDIES AND EX- 
PERIMENTAL AND THEORETICAL DOWNWASH 
AND SIDEWASH BEHIND FIVE POINTED-TIP WINGS 
AT SUPERSONIC SPEEDS. William B. Boatright. 
April 1954. ii, 119p. diagrs., photos. 
(NACA RML54B10) 



AERODYNAMIC CHARACTERISTICS OF A 
CRUCIFORM-WING MISSILE WITH CANARD CON- 
TROL SURFACES AND OF SOME VERY SMALL 
SPAN WING-BODY MISSILES AT A MACH NUMBER 
OF 1.41. M. Leroy a pear man and Ross 5. 
Robinson. April 1954. 27p. diagrs., tabs. 
(NACARML54B11) 



A WIND-TUNNEL INVESTIGATION OF THE USE 
OF SPOILERS FOR OBTAINING STATIC LONGITU- 
DINAL STABILITY OF A CANARD -MISSILE MODEL 
IN REVERSE FLIGHT. Herman S. Fletcher. June 
1954. 15p diagrs.. tab. (NACA RM L54E0t; 



WIND-TUNNEL INVESTIGATION AT A MACH NUM- 
BER OF 2.01 OF THE AERODYNAMIC CHARACTER- 
ISTICS IN COMBINED PITCH AND SIDESLIP OF 
SOME CANARD-TYPE MISSILES HAVING.CRUCI- 
FORM WINGS AND CANARD SURFACES WITH 70° 
DELTA PLAN FORMS. M. Leroy Spearman and 
Cornelius Driver. August 1954. 121p. diagrs., 
tabs. (NACA RM L54F09) 



AERODYNAMIC CHARACTERISTICS AT A MACH 
NUMBER OF 2.01 OF TWO CRUCIFORM MISSILE 
CONFIGURATIONS HAVING 70° DELTA WINGS 
WITH LENGTH-DIAMETER RATIOS OF 14.8 AND 
17.7 WITH SEVERAL CANARD CONTROLS. 
M. Leroy Spearman and Ross B. Robinson. August 
1954. 32p. diagrs., tabs. (NACA RM L54G20) 



EFFECT ON TRANSONIC AND SUPERSONIC DRAG 
OF FUSELAGE GLOVES DESIGNED TO GIVE A 
SMOOTH OVERALL AREA DISTRIBUTION TO A 
SWEPT-WING-BODY COMBINATION. James 
RudyardHall. November 1954. lOp. diagrs., 
photos. (NACA RM L54H30) 



LONGITUDINAL STABILITY CHARACTERISTICS AT 
TRANSONIC SPEEDS OF A CANARD CONFIGURA- 
TION HAVING A 45° SWEPTBACK WING OF ASPECT 
RATIO 6.0 AND NACA 65A009 AIRFOIL SECTION. 
A. James Vitale and John C McFall, Jr. November 
1954. 24p. diagrs., photos., tab. 
(NACA RM L 54101) 



126 



(1) AERODYNAMICS 



PRELIMINARY LOW-SPEED WIND-TUNNEL INVES- 
TIGATION OF SOME ASPECTS OF THE AERODY- 
NAMIC PROBLEMS ASSOCIATED WITH MISSILES 
CARRIED EXTERNALLY IN POSITIONS NEAR AIR- 
PLANE WINGS. William J. Alford, Jr., H. Norman 
Silvers, and Thomas J. King, Jr. December 1954. 
30p. diagrs., photos., tab. (NACA RM L54J20) 



EXPERIMENTAL AERODYNAMIC FORCES AND 
MOMENTS AT LOW SPEED OF A MISSILE MODEL 
DURING SIMULATED LAUNCHING FROM THE 
MIDSEMISPAN LOCATION OF A 45° SWEPTBACK 
WING-FUSELAGE COMBINATION. William J. 
Alford. Jr.. H. Norman Silvprs. anri Thnmafl .T. 
King, Jr. February 1955. 36p. diagrs., photo., 
tabs. (NACA RM L54Klla) 



A THEORKTICAl. ANALYSIS OF A SIMPLE AERO- 
DYNAMIC DEVICE TO IMPROVE THE LONGITUDI- 
NAL DAMPING OF A CRUCIFORM MISSILE CON- 
FIGURATION AT SUPERSONIC SPEEDS. James E. 
ClenuMits: October 1955. 36 p. diagrs., tab. 
(NACA RM L55H31) 



AN EVALUATION OF AN AEROMECHANIC A L 
METHOD OF MINIMIZING SERVO-MISSILE 
TRANSFER-FUNCTION VARIATIONS WITH FLIGHT 
CONDITION. Martin L. Nason. April 1956. 41p. 
diagrs.. tabs. (NACA RM L58A31) 



WIND-TUNNEL INVESTIGATION OF A RAM-JET 
MISSILE MODEL HAVING A WING AND CANARD 
SURFACES OF DELTA PLAN FORM WITH 70° 
SWEPT LEADING EDGES. FORCE AND MOMENT 
CHARACTERISTICS AT COMBINED ANGLES OF 
PITCH AND SIDESLD? FOR MACH NUMBER 2.01. 
Cornelius Driver and Clyde V. Hamilton. April 
1956. 67p. diagrs., photo., tabs. 
(NACARM L56B21) 



A BRIEF SUMMARY OF EXPERIENCE IN BOOSTING 
AERODYNAMIC RESEARCH MODELS. Joseph G, 
Thibodaux, Jr. (Report is basis of talk presented 
at the thirtieth meeting of Bumblebee Aerodynamics 
Panel, Buffalo, New York, January 4, 1956.) July 
1956. 21p. diagrs., photos. (NACA RM L56E28) 



NONLIFTING WING-BODY COMBINATIONS WITH 
CERTAIN GEOMETRIC RESTRAINTS HAVING 
MINIMUM WAVE DRAG AT LOW SUPERSONIC 
SPEEDS. Harvard Lomax. 1957. 11, Up. diagrs. 
(NACARept. 1297. Supersedes TN 3667) 



LIFT AND CENTER OF PRESSURE OF WING-BODY- 
TAIL COMBINATIONS AT SUBSONIC, TRANSONIC, 
AND SUPERSONIC SPEEDS. William C. Pitts, Jack 
N. Nielsen, and George E. Kaattari. 1957. it, 70p. 
diagrs., tabs. (NACA Rept. 1307) 



CONTRIBUTION OF THE WING PANELS TO THE 
FORCES AND MOMENTS OF SUPERSONIC WING- 
BODY COMBINATIONS AT COMBINED ANGLES. 
J. Richard Spahr. January 1958. 62p. diagrs., 
photo., tabs. (NACA TN 4146) 



(1.7.2.1. 1) 

Wing-Body 



LARGE-SCALE FLIGHT MEASUREMENTS OF 
ZERO-LIFT DRAG AT MACH NUMBERS FROM 0.90 
TO 1 .95 OF AN ARROW WING IN COMBINATION 
WITH A SMALL BODY. Warren Gillespie, Jr., and 
Richard G. Arbic. January 12, 1951. 17p. diagrs., 
photos . , tab . (NACA RM L50K28a) 



LIFT, DRAG, AND PITCHING MOMENT OF LOW- 
ASPECT -RATIO WINGS AT SUBSONIC AND SUPER- 
SONIC SPEEDS - TWISTED AND CAMBERED TRI- 
ANGULAR WING OF ASPECT RATIO 2 WITH NACA 
0003-63 THICKNESS DISTRIBUTION. Charles F. 
Hall and John C . Heitmeyer. June 12, 1951. 24p. 
diagrs., photo., tab. (NACA RM A51E01) 



LIFT, DRAG, AND PITCHmG MOMENT OF LOW- 
ASPECT-RATIO WINGS AT SUBSONIC AND SUPER- 
SONIC SPEEDS - TWISTED AND CAMBERED TRI- 
ANGULAR WING OF ASPECT RATIO 2 WITH NACA 
0005-63 THICKNESS DISTRIBUTION. John C. 
Heitmeyer and Robert B. Petersen. April 1952. 
20p. diagrs., tabs. (NACA RM A52B08) 



LARGE-SCALE FLIGHT MEASUREMENTS OF 
ZERO-LIFT DRAG OF 10 WING-BODY CONFIGURA- 
TIONS AT MACH NUMBERS FROM 0.8 TO 1.6. 
John D. Morrow and Robert L. Nelson. January 
1958. 53p. diagrs., photo., tabs. 
(NACA RM L 5 2D 18a) 



WIND-TUNNEL INVESTIGATION OF THE VORTEX 
WAKE AND DOWNWASH FIELD BEHIND TRIANGU- 
LAR WINGS AND WING-BODY COMBINATIONS AT 
SUPERSONIC SPEEDS. J. Richard Spahr and 
Robert R. Dickey. June 1953. 92p. diagrs., 
photos., tabs. (NACA RM A53D10) 



LIFT, DRAG, AND HINGE MOMENTS AT SUPER- 
SONIC SPEEDS OF AN ALL-MOVABLE TRIANGULAR 
WING AND BODY COMBINATION. William C Drake. 
September 1953. 38p. diagrs., photos., tabs. 
(NACA RM A53F22) 



A METHOD FOR ESTIMATING THE ROLLING MO- 
MENTS CAUSED BY WING-TAIL INTERFERENCE 
FOR MISSILE AT SUPERSONIC SPEEDS. Sherman 
Edwards and Katsumi Hikido. November 1953. 68p. 
diagrs., tabs. (NACA RM A53H18) 



A FLIGHT INVESTIGATION AT TRANSONIC SPEEDS 
OF THE AERODYNAMIC CHARACTERISTICS OF A 
MODEL HAVING A THIN UNSWEPT WING OF 
ASPECT RATIO 3.1. Maurice D. White. Adgust 
1954. 41p. diagrs., photo., tabs. 
(NACA RM A54E12) 



AN EXPERIMENTAL INVESTIGATION OF REDUC- 
TION IN TRANSONIC DRAG RISE AT ZERO LIFT BY 
THE ADDITION OF VOLUME TO THE FUSELAGE 
OF A WING -BODY -TAIL CONFIGURATION AND A 
COMPARISON WITH THEORY. George H, Holdaway. 
August 1954. 35p. diagrs., photos., tabs. 
(NACA RM A54F22) 



PRELIMINARY LOW-SPEED WIND-TUNNEL INVES- 
TIGATION OF SOME ASPECTS OF THE AERODY- 
NAMIC PROBLEMS ASSOCIATED WITH MISSILES 
CARRIED EXTERNALLY IN POSTTK>NS NEAR AIR- 
PLANE WINGS. William J. Alford, Jr., H. Norman 
Silvers, and Thomas J. King, Jr. December 1954. 
30p. diagrs., photos., tab. (NACARM L54J20) 



EXPERIMENTAL AERODYNAMIC FORCES AND 
MOMENTS AT LOW SPEED OF A MISSILE MODEL 
DURING SIMULATED LAUNCHING FROM THE 
MIDSEMISPAN LOCATION OF A 45° SWEPTBACK 
WING-FUSELAGE COMBINATION. William J. 
Alford, Jr., H. Norman Silvers, and Thomas J. 
King, Jr. February 1955. 36p. diagrs., photo., 
tabs. (NACA RM L54Klla) 



FLUTTER EXPERIENCES WITH THIN POINTED-TTP 
WINGS DURING FLIGHT TESTS OF ROCKET- 
PROPELLED MODELS AT MACH NUMBERS FROM 
0.8 TO 1.95. Harvey A. WaUskog. April 1955. 
32p. diagrs., photos., tabs. (NACARM L55A14) 



(1) AERODYNAMICS 



127 



INVESTIGATION OF INTERFERENCE LIFT, DRAG, 
AND PITCHING MOMENT OF A SERIES OF TRI- 
ANGULAR WING AND BODY COMBINATIONS AT A 
MACH NUMBER OF 1.62. Donald E. Coletti. May 
1955. 49p. diagrs., photo., tabs. 
(NACA RM L55B25) 



ADDITIONAL COMPARISONS BETWEEN COMPUTED 
AND MEASURED TRANSONIC DRAG-RISE COEFFI- 
CIENTS AT ZERO LIFT FOR WING-BODY-TAIL 
CONFIGURATIONS. George H. Holdaway. August 
1955. 43p. diagrs., photo., tabs. 
(NACA RM A55F06) 



INVESTIGATION OF INTERFERENCE LIFT, DRAG, 
AND PITCHING MOMENT OF A SERIES OF 
TRIANGULAR-WING AND BODY COMBINATIONS 
AT A MACH NUMBER OF 1.94. Donald E. Coletti. 
December 1955. 52p. diagrs., photo., tabs. 
(NACA RM L55I14) 



AERODYNAMICS OF BODIES, WINGS, AND WING- 
BODY COMBINATIONS AT HIGH ANGLES OF AT- 
TACK AND SUPERSONIC SPEEDS. Jack N. 
Nielsen, J. Richard Spahr, and Frank Cento lanzi. 
February 1956. 12p. diagrs. (NACA RM A55L13c) 



THE EFFECT OF EXTERNAL STIFFENING RIBS ON 
THE ROLLING POWER OF AILERONS ON A SWEPT 
WING. Emily W. Stephens. October 1956. 15p. 
diagrs , photo., tab. (NACA RM L56D19) 



SOME CONSIDERATIONS OF THE INFLUENCE OF 
BODY CROSS-SECTIONAL SHAPE ON THE LIFTING 
EFFICIENCY OF WING-BODY COMBINATIONS AT 
SUPERSONIC SPEEDS. E. B. Klunker and Keith C. 
Harder. October 1956. 20p. diagrs. 
(NACA RM L56H30) 



A THEORETICAL STUDY OF THE AERODYNAMICS 
OF SLENDER CRUCIFORM-WING ARRANGEMENTS 
AND THEIR WAKES. John R. Spreiter and Alvln H. 
Sacks. 1957. ii, 31p. diagrs., photos., tabs. 
(NACA Rept. 1296. Supersedes TN 3528) 



ELLD7TIC CONES ALONE AND WITH WINGS AT 
SUPERSONIC SPEEDS. Leland H. Jorgensen. 
October 1957. 55p. diagrs., photos. 
(NACA TN 4045) 



A BODY MODIFICATION TO REDUCE DRAG DUE 
TO WEDGE ANGLE OF WING WITH UNSWEPT 
TRAILING EDGE. William C. Pitts and Jack N. 
Nielsen. July 1958. 13p. (NACA TN 4277) 



SUPERSONIC WAVE INTERFERENCE AFFECTING 
STABILITY. EugeneS. Love. September 1958. 
19p. diagrs., photos. (NACA TN 4358. Supersedes 
RM L55L14a) 



COMPARISON OF SHOCK -EXPANSION THEORY 
WITH EXPERIMENT FOR THE LIFT, DRAG, AND 
PITCHING-MOMENT CHARACTERISTICS OF TWO 
WING-BODY COMBINATIONS AT M = 5.0. 
Raymond C. Savin. September 1958. 13p. diagrs. 
(NACA TN 4385) 



(1.7.2.1.2) 
Tail -Body 



LARGE-SCALE FLIGHT MEASUREMENTS OF 
ZERO-LIFT DRAG AT MACH NUMBERS FROM 0.90 
TO 1.95 OF AN ARROW WING IN COMBINATION 
WITH A SMALL BODY. Warren Gillespie, Jr., and 
Richard G. Arbic. January 12, 1951. 17p. diagrs., 
photos . , tab . (NACA RM L50K28a) 



TRANSONIC FREE-FLIGHT DRAG RESULTS OF 
FULL-SCALE MODELS OF 16-INCH-DLAMETER 
RAM-JET ENGINES. Wesley E. Messing and 
LorenW. Acker. April 1952. 17p. dUgrs. 
(NACARME52B19) 



EXPERIMENTAL INVESTIGATION OF THE STATIC 
AERODYNAMIC AND DYNAMIC DAMPING-IN-ROLL 
CHARACTERISTICS OF AN 8-CM AIRCRAFT 
ROCKET WITH SOLID AND SLOTTED FINS. Robert 
S. Chubb. June 1952. ii, 43p. diagrs., photo. 
(NACA RM A52C04) 



TRANSONIC FREE-FLIGHT INVESTIGATION OF THE 
TOTAL DRAG AND OF THE COMPONENT DRAGS 
(COWL PRESSURE, ADDITIVE, BASE, FRICTION, 
AND INTERNAL) ENCOUNTERED BY A 18-INCH- 
DIAMETER RAM -JET ENGINE FOR MACH NUMBERS 
FROM 0.80 TO 1 .43 . Wesley E . Messing and 
Leonard Rabb. August 1952. 34p. diagrs., photos. 
(NACA RM E52F02) 



EXPLORATORY ROCKET FLIGHT TESTS TO IN- 
VESTIGATE THE USE OF A FREELY SPINNING 
MONOPLANE TAIL FOR STABILIZING A BODY- 
Paul E. Purser and Joseph E. Stevens. October 
1952. 25p. diagrs., photos., tab. 
(NACA RM L 5210 5a) 



LARGE-SCALE FLIGHT MEASUREMENTS OF 
ZERG-LIFT DRAG OF 10 WING -BODY CONFIGURA- 
TIONS A? MACH NUMBERS FROM 0.8 TO 1.6. 
John D. Morrow and Robert L. Nelson. January 
1958. 53p, diagrs,, photo., tabs. 
(NACA RM L52D1RA) 



ROCKET-POWERED MODEL INVESTIGATION OF 
LIFT, DRAG, AND STABILITY OF A BODY -TAIL 
CONFIGURATION AT MACH NUMBERS FROM 0.8 
TO 2.3 AND ANGLES OF ATTACK BETWEEN ±6.5°. 
Warren Gillespie, Jr., and Albert E. Dietz. April 
1954. 42p. diagrs., photos., tabs. 
(NACA RM L54C04) 



PRELIMINARY LOW-SPEED WIND-TUNNEL INVES- 
TIGATION OF SOME ASPECTS OF fHE AERODY- 
NAMIC PROBLEMS ASSOCIATED WITH MISSILES 
CARRIED EXTERNALLY IN POSITIONS NEAR AIR- 
PLANE WINGS. William J. Alford, Jr., H. Norman 
Silvers, and Thomas J. King, Jr. December 1954. 
30p. diagrs., photos., tab. (NACA RM L54J20) 



EXPERIMENTAL AERODYNAMIC FORCES AND 
MOMENTS AT LOW SPEED OF A MISSILE MODEL 
DURING SIMULATED LAUNCHING FROM THE 
MIDSEMISPAN LOCATION OF A 45° SWEPTBACK 
WING-FUSELAGE COMBINATION. William J. 
Alford, Jr., H. Norman Silvers, and Thomas J. 
King, Jr. February 1955. 36p. diagrs., photo., 
tabs. (NACA RM L54Klla) 



PRELIMINARY FREE-FLIGHT STUDY OF THE 
DRAG AND STABILITY OF A SERIES OF SHORT- 
SPAN MISSILES AT MACH NUMBERS FROM 0.9 TO 
1.3. James Rudyard Hall. February 1956. Up. 
diagrs., photo. (NACA RM L55J13) 



AN EXPERIMENTAL STUDY OF THE 2ERO- 
ANGLE-OF -ATTACK TRANSONIC DRAG ASSOCI- 
ATED WITH THE VERTICAL POSITION OF A HORI- 
ZONTAL TAIL AT ZERO INCIDENCE. Robert R. 
Howell. October 1956. 21p. diagrs., photos., tab. 
(NACA RM L56H07) 



128 



(1) AERODYNAMICS 



(1.7.2.1.3) 
Jet Interference 



INVESTIGATION AT MACH NUMBER 1.91 OF SIDE 
AND BASE PRESSURE DISTRIBUTIONS OVER CONI- 
CAL BOATTAILS WITHOUT AND WITH JET FLOW 
ISSUING FROM BASE. Edgar M. Cortright, Jr., and 
Albert H. Schroeder. September 1951. 59p. diagrs., 
photos. (NACA RM E51F26) 



SPREADING OF EXHAUST JET FROM 16-INCH RAM 
JET AT MACH NUMBER 2.0. Fred Wilcox and 
Donald Pennington. August 1952. I4p. diagrs., 
photo., tab. (NACA RM E52F25) 



JET EFFECTS ON FLOW OVER AFTERBODIES IN 
SUPERSONIC STREAM. Edgar M. Cortright, Jr., 
and Fred D. Kochendorfer. November 1953. 31p. 
diagrs., photos. (NACA RM E53H25) 



EFFECT OF JET -NOZZLE-EXPANSION RATIO ON 
DRAG OF PARABOLIC AFTERBODIES. Gerald W. 
Englert, Donald J. Vargo, and Robert W. Cubbison. 
April 1954. 26p. diagrs., photos. 
(NACA RM E54B12) 



ROCKET-POWERED MODEL INVESTIGATION OF 
LIFT, DRAG, AND STABILITY OF A BODY -TAIL 
CONFIGURATION AT MACH NUMBERS FROM 0.8 
TO 2.3 AND ANGLES OF ATTACK BETWEEN ±6.50. 
Warren Gillespie, Jr., and Albert E. Dietz. April 
1954. 42p. diagrs., photos., tabs. 
(NACA RM L54C04) 



EXPERIMENTAL EFFECTS OF PROPULSIVE JETS 
AND AFTERBODY CONFIGURATIONS ON THE 
ZERO-LIFT DRAG OF BODIES OF REVOLUTION AT 
A MACH NUMBER OF 1.59. Carlos A. de Moraes 
andAlbinM. Nowitzky. April 1954. 32p. diagrs., 
photos. (NACA RM L54C16) 



PUMPING AND DRAG CHARACTERISTICS OF AN 
AIRCRAFT EJECTOR AT SUBSONIC AND SUPER- 
SONIC SPEEDS. Gerald C. Gorton. June 1954. 
19p. diagrs. (NACA RM E54D06) 



TRANSONIC FLIGHT TEST OF A ROCKET- 
POWERED MODEL TO DETERMINE PROPULSIVE 
JET INFLUENCE ON THE CONFIGURATION DRAG. 
Carlos A. deMoraes. June 1954. 16p. diagrs., 
photo. (NACA RM L54D27) 



INVESTIGATION AT SUPERSONIC SPEEDS OF THE 
EFFECT OF JET MACH NUMBER AND DIVER- 
GENCE ANGLE OF THE NOZZLE UPON THE PRES- 
SURE OF THE BASE ANNULUS OF A BODY OF 
REVOLUTION. August F. Bromm, Jr., and Robert 
M. O'Donnell. December 1954. 24p. diagrs., 
photos. (NACA RM L 5 41 16) 



JET EFFECTS ON LONGITUDINAL TRIM OF AN 
AIRPLANE CONFIGURATION MEASURED AT MACH 
NUMBERS BETWEEN 1.2 AND 1.8. Robert F. Peck. 
January 1955. 17p. diagrs., photos. 
(NACA RM L54J29a) 



SOME STUDIES OF AXISYMMETRIC FREE JETS 
EXHAUSTING FROM SONIC AND SUPERSONIC 
NOZZLES INTO STILL AIR AND INTO SUPERSONIC 
STREAMS. Eugene S. Love and Carl E. Grigsby. 
May 1955. ii, 178p. diagrs., photos., tabs. 
(NACA RM L54L31) 



A FREE-FLIGHT INVESTIGATION OF THE EFFECTS 
OF SIMULATED SONIC TURBOJET EXHAUST ON 
THE DRAG OF A BOATTAIL BODY WITH VARIOUS 
JET SIZES FROM MACH NUMBER 0.87 TO 1.50. 
Ralph A. Falanga. August 1955. 23p. diagrs., 
photos., tab. (NACA RM L55F09a) 



FREE -FLIGHT TESTS TO DETERMINE THE 
POWER-ON AND POWER -OFF PRESSURE DISTRI- 
BUTION AND DRAG OF THE NACA RM-10 RE- 
SEARCH VEHICLE AT LARGE REYNOLDS NUM- 
BERS BETWEEN MACH NUMBERS 0.8 AND 3.0. 
Sherwood Hoffman. September 1955. 55p. diagrs., 
photos., 3 tabs. (NACA RM L55H02) 



INITIAL INCLINATION OF THE MIXING BOUNDARY 
SEPARATING AN EXHAUSTING SUPERSONIC JET 
FROM A SUPERSONIC AMBIENT STREAM. 
EugeneS. Love. January 1956. 30p. diagrs. 
(NACA RM L55J14) 



RESULTS OF ROCKET MODEL TEST OF AN AIR- 
PLANE CONFIGURATION HAVING AN ARROW WING 
AND SLENDER FLAT -SIDED FUSELAGE. LOT, 
DRAG, LONGITUDINAL STABILITY, LATERAL 
FORCE, AND JET EFFECTS AT MACH NUMBERS 
BETWEEN 1.0 AND 2.3. Robert F. Peck. 
February 1956. 26p. diagrs., photo. 
(NACARM L55L29) 



A FREE -FLIGHT INVESTIGATION OF THE EF- 
FECTS OF A SONIC JET ON THE TOTAL-DRAG 
AND BASE -PRESSURE COEFFICIENTS OF A BOAT- 
TAIL BODY OF REVOLUTION FROM MACH NUM- 
BER 0.83 TO 1.70. Ralph A. Falanga. March 1966. 
18p. diagrs., photo., tab. (NACARM L55L21) 



INTERACTION OF AN EXHAUST JET AND ELE- 
MENTARY CONTOURED SURFACES LOCATED IN A 
SUPERSONIC AIR STREAM. Joseph F. Wasserbauer 
and Gerald W. Englert. April 1956. 20p. diagrs., 
photo. (NACA RM E56A16) 



TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF A HEATBD PROPULSIVE JET 
ON THE PRESSURE DISTRIBUTION ALONG A 
FUSELAGE OVERHANG. Elden S. Cornette and 
Donald H. Ward. April 1956. 42p. diagrs., photos., 
tab. (NACA RM L 56 A 27) 



A BRIEF SUMMARY OF EXPERIENCE IN BOOSTING 
AERODYNAMIC RESEARCH MODELS. Joseph G. 
Thibodaux, Jr. (Report is basis of talk presented 
at the thirtieth meeting of Bumblebee Aerodynamics 
Panel, Buffalo, New York, January 4, 1956.) July 
1956. 21p. diagrs., photos. (NACA RM L56E28) 



BOUNDARIES OF SUPERSONIC AXEYMMETRIC 
FREE JETS. EugeneS. Love, Mildred J. Woodling, 
and Louise P. Lee. October 1956. 98p. diagrs. 
(NACA RM L56G18) 



SHAPE OF INITIAL PORTION OF BOUNDARY OF 
SUPERSONIC AXISYMMETRIC FREE JETS AT 
LARGE JET PRESSURE RATIOS. Eugene S. Love 
and Louise P. Lee. January 1958. 29p. diagrs. 
(NACA TN 4195) 



SUPERSONIC WAVE INTERFERENCE AFFECTING 
STABILITY. Eugene S. Love. September 1958. 
19p. diagrs., photos. (NACA TN 4358. Supersedes 
RM L55Ll4a) 



129 



(1) AERODYNAMICS 



(1.7.2,1.4) 
Wing-Tail-Body 



AN INVESTIGATION AT MACH NUMBERS OF 1.62 
AND 1.93 OF THE LIFT EFFECTIVENESS AND 
INTEGRATED DOWNWASH CHARACTERISTICS OF 
SEVERAL IN-LINE MISSILE CONFIGURATIONS 
HAVING EQUAL-SPAN WINGS AND TAILS . Carl E . 
Grigsby. April 1952. 75p. diagrs., tabs. 
(NACA RM L52A02) 



PERFORMANCE CHARACTERISTICS OF CANARD- 
TYPE MISSILE WITH VERTICALLY MOUNTED 
NACELLE ENGINES AT MACH NUMBERS 1.5 TO 
2.0. Leonard J. Obery and Howard S. Krasnow.- 
September 1952. 25p. diagrs. (NACA RM E52H08) 



PERFORMANCE CHARACTERISTICS OT CANARD- 
TYPE MISSUJE WITH WING-MOUNTED NACELLE 
ENGINES AT MACH NUMBERS 1.5 TO 2.0. Emil J. 
Kremzier and Joseph Davids. November 1952. 
30p. diagrs., tab. (NACA RM E52J08) 



SOME APPROXIMATE METHODS FOR ESTIMATING 
THE EFFECTS OF AEROELASTIC BENDING OF 
ROCKET -PROPELLED MODEL-BOOSTER COMBI- 
NATIONS. Richard G. Arbic, George White, and 
Warren Gillespie, Jr. March 1953. 40p. diagrs., 
photos., tabs. (NACA RM L53A0S) 



COMPARISON OF THEORETICAL AND EXPERI- 
MENTAL ZERO-LIFT DRAG-RISE CHARACTERIS- 
TICS OF WING-BODY-TAIL COMBINATIONS NEAR 
THE SPEED OF SOUND. George H. Holdaway. 
October 1953. 27p. diagrs., tab. 
(NACA RM A53H17) 



A FLIGHT INVESTIGATION AT MACH NUMBERS 
FROM 0.67 TO 1.81 OF THE LONGITUDINAL 
STABILITY AND CONTROL CHARACTERISTICS OF 
A 60° DELTA- WING MISSILE CONFIGURATION 
HAVING AN ALL-MOVABLE TAIL. Martin T. 
Moul and Hal T. Baber, Jr. October 1953. 43p. 
diagrs., photo. (NACA RM L53G29) 



A METHOD FOR ESTIMATING THE ROLLING MO- 
MENTS CAUSED BY WING-TAIL INTERFERENCE 
FOR MISSILE AT SUPERSONIC SPEEDS. Sherman 
Edwards and Katsumi Hikido. November 1953. 68p 
diagrs., tabs. (NACA RM A53H18) 



A WIND-TUNNEL INVESTIGATION OF THE USE 
OF SPOILERS FOR OBTAINING STATIC LONGITU- 
DINAL STABILITY OF A CANARD -MISSILE MODEL 
IN REVERSE FLIGHT. Herman S. Fletcher. June 
1954. 15p. diagrs., tab. (NACA RM L54E05) 



A FLIGHT INVESTIGATION AT TRANSONIC SPEEDS 
OF THE AERODYNAMIC CHARACTERISTICS OF A 
MODEL HAVING A THIN UNSWEPT WING OF 
ASPECT RATIO 31. Maurice D. White. August 
1954. 41p. diagrs., photo., tabs. 
(NACA RM A54E12) 



AN EXPERIMENTAL INVESTIGATION OF REDUC- 
TION IN TRANSONIC DRAG RISE AT ZERO LIFT BY 
THE ADDITION OF VOLUME TO THE FUSELAGE 
OF A WING -BODY -TAIL CONFIGURATION AND A 
COMPARISON WITH THEORY. George H. Holdaway. 
August 1954. 35p. diagrs., photos., tabs. 
(NACA RM A54F22) 



PRELIMINARY LOW-SPEED WIND-TUNNEL INVES- 
TIGATION OF SOME ASPECTS OF THE AERODY- 
NAMIC PROBLEMS ASSOCIATED WITH MISSILES 
CARRIED EXTERNALLY IN POSITIONS NEAR AIR- 
PLANE WINGS. William J. Alford, Jr., H. Norman 
Silvers, and Thomas J. King, Jr. December 1954. 
30p. diagrs., photos., tab. (NACA RM L54J20) 



A FLIGHT INVESTIGATION AT TRANSONIC 
SPEEDS AND SMALL ANGLES OF ATTACK OF THE 
AERODYNAMIC CHARACTERISTICS OF A MODEL 
HAVING A 45° SWEPTBACK WING OF ASPECT 
RATIO 3 WITH AN NACA 64A006 AIRFOIL SECTION. 
George H. Holdaway. January 1955. 32p. diagrs., 
photo., tab. (NACA RM A54I17) 



EXPERIMENTAL AERODYNAMIC FORCES AND 
MOMENTS AT LOW SPEED OF A MISSILE MODEL 
DURING SIMULATED LAUNCHING FROM THE 
MIDSEMISPAN LOCATION OF A 45° SWEPTBACK 
WING-FUSELAGE COMBINATION. William J. 
Alford, Jr., H. Norman Silvers, and Thomas J. 
King, Jr. February 1955. 36p. diagrs., photo., 
tabs. (NACA RM L54Klla) 



A FLIGHT INVESTIGATION AT TRANSONIC SPEEDS 
OF A MODEL HAVING A TRIANGULAR WING OF 
ASPECT RATIO 4. Loren G. Bright. March 1955. 
40p. diagrs., photos., tabs. (NACA RM A54L27) 



ADDITIONAL COMPARISONS BETWEEN COMPUTED 
AND MEASURED TRANSONIC DRAG-RISE COEFFI- 
CIENTS AT ZERO LIFT FOR WING-BODY -TAIL 
CONFIGURATIONS. George H. Holdaway. August 
1955. 43p. diagrs., photo., tabs. 
(NACA RM A55F06) 



A FLIGHT INVESTIGATION AT TRANSONIC SPEEDS 
OF A MODEL HAVING A TRIANGULAR WING OF 
ASPECT RATIO 2. Maurice D. White. September 
1955. 39p. diagrs., photo., tabs. 
(NACA RM A55F21) 



DETERMINATED OF VORTEX PATHS BY SERIES 
EXPANSION TECHNIQUE WITH APPLICATION TO 
CRUCIFORM WINGS. Alberto Y . Alksne . 1957. 
ill, 13p. diagrs., photos. (NACA Rept. 1311. 
Supersedes TN 3670) 



(1.7.2.2) 

SPECIFIC MISSILES 



ALTITUDE -TEST -CHAMBER INVESTIGATION OF 
PERFORMANCE OF A 28-INCH RAM-JET ENGINE. 
I - COMBUSTION AND OPERATIONAL PERFORM- 
ANCE OF FOUR COMBUSTION- CHAMBER CONFIG- 
URATIONS. W. L. Jones, T. B. Shillito, and J. G. 
Henzel, Jr. August 23, 1950. 53p. diagrs., photos. 
(NACA RM E50F16) 



ALTITUDE-TEST-CHAMBER INVESTIGATION OF 
PERFORMANCE OF A 28-INCH RAM -JET ENGINE. 
D - EFFECTS OF GUTTER WIDTH AND BLOCKED 
AREA ON OPERATING RANGE AND COMBUSTION 
EFFICIENCY. T. B. Shillito, W. L. Jones, and 
R. W. Kahn. November 6, 1950. 58p. diagrs. 
(NACA RM E50H21) 



ALTITUDE-TEST-CHAMBER INVESTIGATION OF 
PERFORMANCE OF A 28-INCH RAM -JET ENGINE. 
IU - COMBUSTION AND OPERATIONAL PERFORM- 
ANCE OF THREE FLAME HOLDERS WITH A CEN- 
TER PILOT BURNER. Thomas B. Shillito, George 
G. Younger, and James G. Henzel, Jr. February 6, 
1951. 30p. diagrs. (NACA RM E50J20) 



130 



(1) AERODYNAMICS 



ALTITUDE-TEST-CHAMBER INVESTIGATION OF 
PERFORMANCE OF A 28-INCH RAM -JET ENGINE. 
IV - EFFECT OF INLET-AIR TEMPERATURE, 
COMBUSTION -CHAMBER-INLET MACH NUMBER, 
AND FUEL VOLATILITY ON COMBUSTION PER- 
FORMANCE. Robert W. Kahn, Shigeo Nakanishi, 
and James L. Harp, Jr. July 1951. 27p. diagrs. 
(NACARM E51D11) 



THE EFFECT OF VARIOUS MISSILE CHARACTER- 
ISTICS ON AIRFRAME FREQUENCY RESPONSE. 
Howard F. Matthews and Walter E . McNeill. 
January 1952. 16p. diagrs. (NACA RM A51L17a) 

PRELIMINARY FREE-FLIGHT INVESTIGATION OF 
THE ZERO-LIFT DRAG PENALTIES OF SEVERAL 
MISSILE NOSE SHAPES FOR INFRARED SEEKING 
DEVICES. Roberto. Piland. December 1952. 
22p. diagrs., photos, (NACA RM L52F23) 



INVESTIGATION OF THE DRAG OF BLUNT -NOSED 
BODffiS OF REVOLUTION IN FREE FLIGHT AT 
MACH NUMBERS FROM 0.6 TO 2.3. Harvey A. 
Wallskog and Roger G. Hart. June 1953. 28p. 
diagrs., photos., tab. (NACA RM L53D14a) 



ROCKET-MODEL INVESTIGATION TO DETERMINE 
THE HINGE-MOMENT AND NORMAL-FORCE 
PROPERTIES OF A FULL-SPAN, CONSTANT- 
CHORD, PARTIALLY BALANCED TRAILING -EDGE 
CONTROL ON A 60° CLIPPED DELTA WING BE- 
TWEEN MACH NUMBERS OF 0.50 AND 1.28. 
C. William Martz and John W. Goslee. October 
1953. 33p. diagrs., photos., tab. 
(NACA RM L53I04) 



PRELIMINARY INVESTIGATION OF THE EFFECTS 
OF SEVERAL SEEKER-NOSE CONFIGURATIONS ON 
THE LONGITUDINAL CHARACTERISTICS OF A 
CANARD-TYPE MISSILE AT A MACH NUMBER OF 
1.60. A. Warner Robins. October 1953. 25p. 
diagrs., photos., tabs. (NACARM L53I18) 



EFFECT OF LARGE DEFLECTIONS OF A CANARD 
CONTROL AND DEFLECTIONS OF A WING-TD? 
CONTROL ON THE STATIC -STABILITY AND 
INDUCED-ROLL CHARACTERISTICS OF A CRUCI- 
FORM CANARD MISSILE AT A MACH NUMBER OF 
2.01. M. Leroy Spearman. December 1953. 20p. 
diagrs., tabs. (NACA RM L53K03) 



ZERO-LIFT DRAG OF SEVERAL CONICAL AND 
BLUNT NOSE SHAPES OBTAINED IN FREE FLIGHT 
AT MACH NUMBERS OF 0.7 TO 1.3. Robert O. 
Piland and Leonard W. Putland. March 1954. Up. 
diagrs., photos., tab. (NACA RM L54A27) 



AERODYNAMIC CHARACTERISTICS OF A 
CRUCIFORM-WING MISSILE WITH CANARD CON- 
TROL SURFACES AND OF SOME VERY SMALL 
SPAN WING-BODY MISSILES AT A MACH NUMBER 
OF 1.41. M. Leroy Spearman and Ross B. 
Robinson. April 1954. 27p. diagrs., tabs. 
(NACARML54B11) 



A WIND-TUNNEL INVESTIGATION OF THE USE 
OF SPOILERS FOR OBTAINING STATIC LONGITU- 
DINAL STABILITY OF A CANARD -MISSILE MODEL 
IN REVERSE FLIGHT. Hermans. Fletcher. June 
1954. 15p. diagrs., tab. (NACA RM L54E05) 



WIND-TUNNEL INVESTIGATION AT A MACH NUM- 
BER OF 2.01 OF THE AERODYNAMIC CHARACTER- 
ISTICS IN COMBINED PITCH AND SIDESLIP OF 
SOME CANARD-TYPE MISSILES HAVING CRUCI- 
FORM WINGS AND CANARD SURFACES WITH 70° 
DELTA PLAN FORMS. M. Leroy Spearman and 
Cornelius Driver. August 1954. 121p. diagrs., 
tabs. (NACA RM L54F09) 



FLIGHT MEASUREMENTS OF AVERAGE SKIN- 
FRICTION COEFFICIENTS ON A PARABOLIC BODY 
OF REVOLUTION (NACA RM-10) AT MACH NUM- 
ERS FROM 1.0 TO 3.7. J. Dan Loposer and 
Charles B. Rumsey. August 1954. 32p. diagrs., 
photos. (NACA RM L54G14) 



AERODYNAMIC CHARACTERISTICS AT A MACH 
NUMBER OF 2.01 OF TWO CRUCIFORM MISSILE 
CONFIGURATIONS HAVING 70° DELTA WINGS 
WITH LENGTH -DIAMETER RATIOS OF 14.8 AND 
17.7 WITH SEVERAL CANARD CONTROLS. 
M. Leroy Spearman and Ross B. Robinson. August 
1954, 32n : diagrs, tabs. (NACA RM L54G20) 



FREE-FLIGHT TESTS TO DETERMINE THE 
POWER-ON AND POWER-OFF PRESSURE DISTRI- 
BUTION AND DRAG OF THE NACA RM-10 RE- 
SEARCH VEHICLE AT LARGE REYNOLDS NUM- 
BERS BETWEEN MACH NUMBERS 0.8 AND 3.0. 
Sherwood Hoffman. September 1955. 55p. diagrs., 
photos., 3 tabs. (NACA RM L55H02) 



WIND-TUNNEL INVESTIGATION OF A RAM -JET 
MISSILE MODEL HAVING A WING AND CANARD 
SURFACES OF DELTA PLAN FORM WITH 70° 
SWEPT LEADING EDGES . FORCE AND MOMENT 
CHARACTERISTICS AT COMBINED ANGLES OF 
PITCH AND SIDESLD? FOR MACH NUMBER 2.01. 
Cornelius Driver and Clyde V. Hamilton. April 
1956. 67p. diagrs., photo., tabs. 
(NACA RM L56B2D 



FLIGHT MEASUREMENTS OF BOUNDARY -LAYER 
TEMPERATURE PROFILES ON A BODY OF REVO- 
LUTION (NACA RM-10) AT MACH NUMBERS FROM 
1.2 TO 3.5. Andrew G. Swanson, James J. Buglia, 
and Leo T. Chauvin. July 1957. 40p. diagrs., 
photos. (NACA TN 4061) 



(1.7.3) 
ROTATING-WING AIRCRAFT 



(1.7.3. 1) 
AUTOGIROS 



FULL-SCALE WIND-TUNNEL TESTS OF THE LON- 
GITUDINAL STABILITY AND CONTROL CHARAC- 
TERISTICS OF THE XV- 1 CONVERTIPLANE IN THE 
AUTOROTATING FLIGHT RANGE. David H. Hickey. 
May 1956. 64p. diagrs., photos., tabs. 
(NACA RM A55K21a) 



(1.7.3.2) 

HELICOPTERS 



ANALYSIS OF A PRESSURE-JET POWER PLANT 
FOR A HELICOPTER. Richard P. Krebs and 
Williams. Miller, Jr. March 1955. 56p. diagrs. 
(NACA RM E54L23) 



FULL-SCALE WIND-TUNNEL TESTS OF THE LON- 
GITUDINAL STABILITY AND CONTROL CHARAC- 
TERISTICS OF THE XV- 1 CONVERTIPLANE IN THE 
AUTOROTATING FLIGHT RANGE. David H. Hickey. 
May 1956. 64p. diagrs., photos., tabs. 
(NACA RM A55K21a) 

EFFECT OF AMBIENT CONDITIONS ON THE PER- 
FORMANCE OF A PRESSURE-JET POWERPLANT 
FOR A HELICOPTER. Richard P. Krebs. June 
1956. 49p. diagrs. (NACA RM E56B21) 



131 



( 1 ) AERODYNAMICS 



EXPLORATORY INVESTIGATION OF A HELICOP- 
TER PRESSURE-JET SYSTEM ON THE LANGLEY 
HELICOPTER TEST TOWER. Robert A. Makofski 
and James P. Shivers. July 1356. 38p. diagrs., 
photo. (NACA RM L56B17) 



EXPERIMENTAL INVESTIGATION OF THE AERO- 
DYNAMIC LOADING ON A HELICOPTER ROTOR 
BLADE IN FORWARD FLIGHT. John P . Rabbott, 
Jr., and Gary B. Churchill. October 1956. 65p. 
diagrs., photos., tabs. (NACA RM L56I07) 



INDUCED VELOCITIES NEAR A LIFTING ROTOR 
WITH NONUNIFORM DISK LOADING. Harry H. 
HeysonandS. Katzoff. 1957. iii, 88p. diagrs., 
photos., tab. (NACA Rept. 1319. Supersedes 
TN 3690; TN 3691} 



FLIGHT AND ANALYTICAL METHODS FOR DETER- 
MINING THE COUPLED VIBRATION RESPONSE OF 
TANDEM HELICOPTERS. John E. Yeates, Jr., 
George W. Brooks, and John C. Houbolt. 1957. iv, 
31p. diagrs., photo., tabs. (NACA Rept. 1326. 
Supersedes TN 3852; TN 3849) 



COMPRESSIBILITY EFFECTS ON A HOVERING 
HELICOPTER ROTOR HAVING AN NACA 0018 ROOT 
AIRFOIL TAPERING TO AN NACA 0012 TIP AIR- 
FOIL. Robert D. Powell, Jr. September 1957. 
25p. diagrs. (NACA RM L57F26) 



FLIGHT INVESTIGATION OF EFFECTS OF ATMOS- 
PHERIC TURBULENCE AND MODERATE MANEU- 
VERS ON BENDING AND TORSIONAL MOMENTS 
ENCOUNTERED BY A HELICOPTER ROTOR BLADE. 

LeRoy H. Ludi. February 1958. 34p. diagrs., 
photo., tab. (NACA TN 4203) 



ANALYSIS OF HARMONIC FORCES PRODUCED AT 
HUB BY IMBALANCES IN HELICOPTER ROTOR 
BLADES. M. Morduchow and A. Muzyka, 
Polytechnic Institute of Brooklyn. April 1958. 37p. 
diagrs. (NACA TN 4226) 



EXPERIMENTAL INVESTIGATION OF THE DRAG 
OF FLAT PLATES AND CYLINDERS IN THE SLIP- 
STREAM OF A HOVERING ROTOR. John W. McKee 
and Rodger L. Naeseth. April 1958. 42p. diagrs., 
photos., tab. (NACA TN 4239) 



FLIGHT INVESTIGATION OF EFFECTS OF 
RETREATING-BLADE STALL ON BENDING AND 
TORSIONAL MOMENTS ENCOUNTERED BY A 
HELICOPTER ROTOR BLADE. LeRoy H. Ludi. 
May 1958. 23p. diagrs., photo. (NACA TN 4254) 



NORMAL COMPONENT OF INDUCED VELOCITY 
FOR ENTIRE FIELD OF A UNIFORMLY LOADED 
LIFTING ROTOR WITH HIGHLY SWEPT WAKE AS 
DETERMINED BY ELECTROMAGNETIC ANALOG. 
Walter Castles, Jr., Howard L. Durham, Jr., and 
Jirair Kevorkian, Georgia Institute of Technology. 
June 1958. 33p. diagrs., photos., tabs. 
(NACA TN 4238) 



WIND-TUNNEL INVESTIGATION OF EFFECTS OF 
SPOILER LOCATION, SPOILER SIZE, AND FUSE- 
LAGE NOSE SHAPE ON DIRECTIONAL CHARACTER- 
ISTICS OF A MODEL OF A TANDEM -ROTOR HELI- 
COPTER FUSELAGE. James L. Williams. July 
1958. 44p. diagrs., photos., tab. (NACA TN 4305) 



FLOW INDUCED BY A ROTOR IN POWER-ON 
VERTICAL DESCENT. Walter Castles, Jr., 
Georgia Institute of Technology. July 1958. 25p. 

diagrs., tabs. (NACA TN 4330) 



LOW TIP MACH NUMBER STALL CHARACTERIS- 
TICS AND HIGH TIP MACH NUMBER COMPRESSI- 
BILITY EFFECTS ON A HELICOPTER ROTOR 
HAVING AN NACA 0009 TIP AIRFOIL SECTION. 
Robert D. Powell, Jr., and Paul J. Carpenter. July 
1958. 28p. diagrs. (NACA TN 4355) 



MATRIX METHOD FOR OBTAINING SPANWISE 
MOMENTS AND DEFLECTIONS OF TORSIONALLY 
RIGID ROTOR BLADES WITH ARBITRARY LOAD- 
INGS. Alton P. Mayo. August 1958. 51p. diagrs., 
tabs. (NACA TN 4304) 



AN EXPERIMENTAL INVESTIGATION OF THE 
EFFECT OF VARIOUS PARAMETERS INCLUDING 
TIP MACH NUMBER ON THE FLUTTER OF SOME 
MODEL HELICOPTER ROTOR BLADES. George W. 
Brooks and John E. Baker. September 1958. 68p. 
diagrs.. photo., tabs- (NACA TN 4005. Supersedes 
RM L53D24) 



EFFECTS OF COMPRESSIBILITY ON ROTOR HOV- 
ERING PERFORMANCE AND SYNTHESIZED BLADE- 
SECTION CHARACTERISTICS DERIVED FROM 
MEASURED ROTOR PERFORMANCE OF BLADES 
HAVING NACA 0015 AIRFOIL TD? SECTIONS. 
James P. Shivers and PauIJ. Carpenter Septemhpr 
1958. 28p. diagrs. (NACA TN 4356) 



LIFT AND PROFILE-DRAG CHARACTERISTICS OF 
AN NACA 0012 AIRFOIL SECTION AS DERIVED 
FROM MEASURED HELICOPTER-ROTOR HOVER- 
ING PERFORMANCE. PaulJ. Carpenter. 
September 1958. 28p. diagrs., photo. 
(NACA TN 4357) 



WIND-TUNNEL TESTS OF A FULL-SCALE HELI- 
COPTER ROTOR WITH SYMMETRICAL AND WITH 
CAMBERED BLADE SECTIONS AT ADVANCE 
RATIOS FROM 0.3 TO 0.4. John L. McCloud m and 
George B. McCullough. September 1958. 33p. 
diagrs., photos., tab. (NACA TN 4367) 



SOME STATIC LONGITUDINAL STABILITY CHAR- 
ACTERISTICS OF AN OVERLAPPED -TYPE TANDEM- 
ROTOR HELICOPTER AT LOW AIRSPEEDS. Robert 
J. Tapscott. September 1958. 27p. diagrs., tabs. 
(NACA TN 4393) 



FLIGHT MEASUREMENTS OF THE VIBRATION 
EXPERIENCED BY A TANDEM HELICOPTER IN 
TRANSITION, VORTEX-RING STATE, LANDING 
APPROACH, AND YAWED FLIGHT. John E. Yeates. 
September 1958. 20p. diagrs. (NACA TN 4409) 



(1.7.5) 
AIRSHIPS 



A FLIGHT EVALUATION AND ANALYSIS OF THE 
EFFECT OF ICING CONDITIONS ON THE ZPG-2 
AIRSHIP. William Lewis and Porter J. Perkins, Jr. 
April 1958. 66p. diagrs., photos., tab. 
(NACA TN 4220) 



132 



(1) AERODYNAMICS 



(1-8) 
Stability and Control 



WIND-TUNNEL TESTS OF A 1/12-SCALE MODEL 
OF THE X-3 AIRPLANE AT SUBSONIC AND SUPER- 
SONIC SPEEDS. Robert N. Olson and Robert S. 
Chubb. September 14, 1951. 11 lp. dlagrs., photo., 
tabs. (NACA RM A51F12) 



HANDLING QUALITIES OF HIGH-SPEED AIRPLANES. 
W. C. Williams and A. S Crossfield. January 1952. 
17p. diagrs. (NACA RM L52A08) 



MEASUREMENTS OBTAINED DURING THE GLIDE- 
FLIGHT PROGRAM OF THE BELL X-2 RESEARCH 
AIRPLANE. Richard E. Day. July 30, 1953. 27p. 
diagrs., photos., tabs. (NACA RM L53G03a) 



A METHOD FOR INCREASING THE EFFECTIVE- 
NESS OF STABILIZING SURFACES AT HIGH SUPER- 
SONIC MACH NUMBERS. Charles H. McLellan. 
August 1954. 14p. diagrs. (NACA RM L54F21) 



RESULTS OF MEASUREMENTS MADE DURING 
THE APPROACH AND LANDING OF SEVEN HIGH- 
SPEED RESEARCH AIRPLANES. Wendell H. 
Still well. February 1955. 25p. diagrs., tab. 
(NACA RM H54K24) 



SOME STATIC LONGITUDINAL STABILITY CHAR- 
ACTERISTICS OF AN OVERLAPPED-TYPE TANDEM- 
ROTOR HELICOPTER AT LOW AIRSPEEDS. Robert 
J. Tapscott. September 1958. 27p. diagrs., tabs. 
(NACA TN 4393) 



(1.8.1) 
STABILITY 



EXPLORATORY ROCKET FLIGHT TESTS TO IN- 
VESTIGATE THE USE OF A FREELY SPINNING 
MONOPLANE TAIL FOR STABILIZING A BODY. 
Paul E. Purser and Joseph E. Stevens. October 
1952. 25p. diagrs., photos., tab. 
(NACA RM L52I05a) 



THE EFFECT OF INITIAL RATE OF SUBSONIC 
DIFFUSION ON THE STABLE SUBCRITICAL MASS- 
FLOW RANGE OF A CONICAL SHOCK DIFFUSER. 
J. C. Nettles. July 1953. 23p. diagrs. 
(NACA RM E53E26) 



SUPERSONIC WAVE INTERFERENCE AFFECTING 
STABILITY. EugeneS. Love, September 1958. 
19p. diagrs., photos. (NACA TN 4358. Supersedes 
RM L55L14a) 



(1-8.1.1) 
STATIC 



ESTIMATED TRANSONIC FLYING QUALITIES OF A 
TAILLESS AIRPLANE BASED ON A MODEL INVES- 
TIGATION. Charles J. Donlan and Richard E . Kuhn. 
June 8, 1949. 63p. diagrs., photos., tabs. 
(NACA RM L9D08) 



FREE-FLIGHT DETERMINATION OF FORCE AND 
STABILITY CHARACTERISTICS OF AN INCLINED 
BODY OF FINENESS RATIO 16.9 AT A MACH NUM- 
BER OF 1.74. Warren Gillespie, Jr. November 
1954. 17p. diagrs., photos., tab. 
(NACA RM L54G28a) 



DATA FROM LARGE-SCALE LOW -SPEED TESTS 
OF AIRPLANE CONFIGURATIONS WITH A THIN 45° 
SWEPT WING INCORPORATING SEVERAL 
LEADING-EDGE CONTOUR MODIFICATIONS. 
William T. Evans. May 1956. llOp. diagrs., 
photo., tabs. (NACA RM A56B17) 



FULL-SCALE WIND-TUNNEL TESTS OF A 35° 
SWEPTBACK-WING AIRPLANE WITH HIGH- 
VELOCITY BLOWING OVER THE TRAILING-EDGE 
FLAPS - LONGITUDINAL AND LATERAL STABIL- 
ITY AND CONTROL. William H. Tolhurst, Jr., 
and Mark W. Kelly. October 1956. 64p. diagrs., 
photo., tabs. (NACA RM A56E24) 



EFFECT OF NOSE SHAPE ON SUBSONIC AERO- 
DYNAMIC CHARACTERISTICS OF A BODY OF 
REVOLUTION HAVING A FINENESS RATIO OF 10.94. 
Edward C. Polhamus. August 1957. 29p. diagrs. 
(NACA RM L57F25) 



EFFECT OF FREQUENCY OF SIDESLIPPING 
MOTION ON THE LATERAL STABILITY DERIVA- 
TIVES OF A TYPICAL DELTA-WING AIRPLANE. 
Jacob H. Lichtenstein and James L. Williams. 
September 1957. 46p. diagrs., photos., tabs. 
(NACA RM L57F07) 



MOTION OF A BALLISTIC MISSILE ANGULARLY 
MISALINED WITH THE FLIGHT PATH UPON EN- 
TERING THE ATMOSPHERE AND ITS EFFECT UP- 
ON AERODYNAMIC HEATING, AERODYNAMIC 
LOADS, AND MISS DISTANCE. H. Julian Allen. 
October 1957. 66p. diagrs., tabs. (NACA TN 4048. 
Supersedes RM A56F15) 



FLIGHT INVESTIGATION OF THE TRANSONIC 
LONGITUDINAL AND LATERAL HANDLING QUAL- 
ITIES OF THE DOUGLAS X-3 RESEARCH AIRPLANE. 
Jack Fischel, Euclid C. Holleman, and Robert A. 
Tremant. December 1957. 61p. diagrs., photos., 
tab. (NACA RM H 5 7105) 



133 



(1) AERODYNAMICS 



AERODYNAMIC EFFECTS CAUSED BY ICING OF 
AN UNSWEPT NACA 65A004 AIRFOIL. Vernon H. 
Gray and Uwe H. von Glahn. February 1958. 47p. 
diagrs., photos., tabs. (NACA TN 4155) 



WIND-TUNNEL INVESTIGATION OF THE AERO- 
DYNAMIC AND STRUCTURAL DEFLECTION CHAR- 
ACTERISTICS OF THE GOODYEAR INFLATOPLANE. 
Bennle W. Cocke, Jr. September 1958. 56p. 
diagrs., photos. (NACA RM L58E09) 



(1.8.1.1*1) 

Longitudinal 



LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS OF AN AIRPLANE MODEL HAVING A 
42.8° SWEPTBACK CIRCULAR-ARC WING WITH 
ASPECT RATIO 4.00, TAPER RATIO 0.50, AND 
SWEPTBACK TAIL SURFACES. Joseph Weil, Paul 
Comisarow, and Kenneth W. Goodson. October 17, 
1947. 84p. diagrs., photos., tab. 
(NACA RM L7G28) 



SUPERSONIC-TUNNEL TESTS OF TWO SUPER- 
SONIC AIRPLANE MODEL CONFIGURATIONS. 
Macon C. Ellis, Jr., Lowell E. Hasel, and Carl E. 
Grigsby. December 31, 1947. 49p. diagrs., 
photos., tab. (NACA RM L7J15) 



RESULTS OBTAINED DURING EXTENSION OF U.S. 
Am FORCE TRANSONIC -FLIGHT TESTS OF XS-1 
AIRPLANE. Harold R. Goodman and Hubert M. 
Drake. November 16, 1948. 12p. diagrs. 
(NACA RM L8I28) 



INVESTIGATION OF THE DYNAMIC LATERAL 
STABDHTY AND CONTROL CHARACTERISTICS OF 
A MODEL OF A FIGHTER AIRPLANE WrTHOUT A 
HORIZONTAL TAIL AND EQUIPPED WITH EITHER 
SINGLE OR TWIN VERTICAL TAILS. John W. 
Draper and Robert W. Rose. November 15, 1949. 
20p. diagrs., photos., tab. (NACA RM L9J07a) 



AERODYNAMIC STUDY OF A WING-FUSELAGE 
COMBINATION EMPLOYING A WrNG SWEPT BACK 
63°. - EFFECTS AT SUBSONIC SPEEDS OF A 
CONSTANT -CHORD ELEVON ON A WING CAM- 
BERED AND TWISTED FOR A UNIFORM LOAD AT 
A LIFT COEFFICIENT OF 0.25. J. Lloyd Jones and 
Fred A. Demele. December 5, 1949. 44p. diagrs., 
photos., tab. (NACA RM A9I27) 



THE EFFECTS OF SCALE AND TEST TECHNIQUE 
ON THE VALIDITY OF SMALL-SCALE MEASURE- 
MENTS OF THE AERODYNAMIC CHARACTERISTICS 
OF A WING WITH THE LEADING EDGE SWEPT 
BACK 630. L . Stewart Rolls. December 9, 1949. 
20p. diagrs., photos. (NACA RM A9J08) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR-ARC SECTIONS AND 40° SWEEPBACK. 
STATIC LONGITUDINAL STABILITY AND CONTROL 
CHARACTERISTICS AT A MACH NUMBER OF 1.40. 
M. Leroy Spearman. April 3, 1950. 27p. diagrs., 
photos., tab. (NACA RM L9L08) 



WIND-TUNNEL TESTS OF A 0.16-SCALE MODEL 
OF THE X-3 AIRPLANE AT HIGH SUBSONIC 
SPEEDS. STABILITY AND CONTROL CHARACTER- 
ISTICS. William T. Hamilton and Joseph W. Cleary. 
April 21, 1950. 129p. diagrs., photos., tabs. 
(NACA RM A50A03) 



WIND-TUNNEL TESTS OF A 0.18-SCALE MODEL 
OF THE X-3 AIRPLANE AT HIGH SUBSONIC SPEEDS. 
- ADDITIONAL STABILITY AND CONTROL CHAR- 
ACTERISTICS AND THE AERODYNAMIC EFFECTS 
OF EXTERNAL STORES AND RAMJETS. Joseph W. 
Cleary and Jack A. Mellenthin. June 13, 1950. 86p. 
diagrs., photos., tabs. (NACA RM A50C30) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR -ARC SECTIONS AND 40° SWEEPBACK. 
STATIC LONGITUDINAL STABILITY AND CONTROL 
CHARACTERISTICS AT A MACH NUMBER OF 1.59. 
M. Leroy Spearman and John H. Hilton, Jr. 
June 29, 1950. 22p. diagrs., photo., tab. 
(NACARML50E12) 



FLIGHT MEASUREMENTS WITH THE DOUGLAS 
D -558 -II (BUAERO NO. 37974) RESEARCH AIR- 
PLANE. DETERMINATION OF THE AERODYNAMIC 
CENTER AND ZERO-LIFT PITCHING -MOMENT 
COEFFICIENT OF THE WING-FUSELAGE COMBI- 
NATION BY MEANS OF TAIL -LOAD MEASURE- 
MENTS IN THE MACH NUMBER RANGE FROM 
0.37 TO 0.87. John P. Mayer, Gecrge M. Valentine, 
and Geraldine C. Mayer. July 11, 1950. 27p. 
diagrs., photos., tab. (NACA RM L50D10) 



A COMPARISON OF THE AERODYNAMIC CHARAC- 
TERISTICS AT TRANSONIC SPEEDS OF FOUR 
WING-FUSELAGE CONFIGURATIONS AS DETER- 
MINED FROM DIFFERENT TEST TECHNIQUES 
Charles J. Don Ian, Boyd C Myers. II, and Axel T 
Mattson. October 4, 1950. 68p. diagrs , photos , 
tabs. (NACA RM L 50 HO 2) 



PRELIMINARY RESULTS OF THE FLIGHT INVES- 
TIGATION BETWEEN MACH NUMBERS OF 0.80 AND 
1.36 OF A ROCKET-POWERED MODEL OF A 
SUPERSONIC AIRPLANE CONFIGURATION HAVING 
A TAPERED WING WITH CUICULAR-ARC SECTIONS 
AND 40° SWEEPBACK. Charles T. D'Alutolo and 
Homer P. Mason. October 31, 1950. 30p. diagrs., 
photos., tab. (NACA RM L 5 OH 29a) 



DETERMINATION OF LONGITUDINAL STABILITY 
OF THE BELL X-l AIRPLANE FROM TRANSIENT 
RESPONSES AT MACH NUMBERS UP TO 1.12 AT 
LIFT COEFFICIENTS OF 0.3 AND 0.6. Ellwyn E. 
Angle and Euclid C. Holleman. November 1 ) 1950. 
22p diagrs. (NACA RM L50I06a) 



AN INVESTIGATION OF THE LONGITUDINAL 
CHARACTERISTICS OF THE X-3 CONFIGURATION 
USING ROCKET-PROPELLED MODELS. PRELIMI- 
NARY RESULTS AT MACH NUMBERS FROM 0.65 
TO 1.25. Jesse L. Mitchell and Robert F. Peck. 
December 1, 1950. 30p. diagrs., photos. 
(NACA RM L50J03) 



FLIGHT MEASUREMENTS WITH THE DOUGLAS 
D-558-II (BUAERO NO. 37974) RESEARCH AIR- 
PLANE. MEASUREMENTS OF WING LOADS AT 
MACH NUMBERS UP TO 0.87. John P. Mayer, 
George M. Valentine, and Beverly J. Swanson. 
December 26, 1950. 35p. diagrs., photos., tab. 
(NACA RM L50H16) 



134 



(1) AERODYNAMICS 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR -ARC SECTIONS AND 40° SWEEPBACK. 
FORCE CHARACTERISTICS OF THE COMPLETE 
■CONFIGURATION AND ITS VARIOUS COMPONENTS 
AT MACH NUMBERS OF 1.40 AND 1.59. Norman F. 
Smith and Jack E. Marte. January 22, 1951. 55p. 
diagrs., photos., tab. (NACA RM L50K14) 



WING -ON AND WING-OFF LONGITUDINAL CHAR- 
ACTERISTICS OF AN AIRPLANE CONFIGURATION 
HAVING A THIN UNSWEPT TAPERED WING OF 
ASPECT RATIO 3, AS OBTAINED FROM ROCKET- 
PROPELLED MODELS AT MACH NUMBERS FROM 
0.8 TO 1.4. Clarence L. Gillis and A. James Vitale. 
March 14, 1951. 52p. diagrs., photos., tabs. 
(NACA RM L50K16) 



LIFT, DRAG, AND PITCHING MOMENT OF LOW- 
ASPECT -RATIO WINGS AT SUBSONIC AND SUPER- 
SONIC SPEEDS - TWISTED AND CAMBERED TRI- 
ANGULAR WING OF ASPECT RATIO 2 WITH NACA 
0003-63 THICKNESS DISTRIBUTION. Charles F. 
Hall and John C . Heitmeyer . June 12, 1951. 24p. 
diagrs., photo., tab. (NACA RM A51E01) 



AN INVESTIGATION OF THE LONGITUDINAL CHAR- 
ACTERISTICS OF THE X-3 CONFIGURATION WITH 
WING AND HORIZONTAL TAIL SURFACES OF 
ASPECT RATIO 3.0 BY MEANS OF ROCKET- 
PROPELLED MODELS. RESULTS AT HIGH LIFT 
COEFFICIENTS. Robert F. Peck and Jesse L. 
Mitchell. August 27, 1951. 34p. diagrs., photos. 
(NACA RM L51G10) 



ANALYSIS OF LONGITUDINAL STABILITY AND 
TRIM OF THE BELL X-l AIRPLANE AT A LIFT 
COEFFICIENT OF 0.3 TO MACH NUMBERS NEAR 
1.05. Hubert M. Drake, JohnR. Carden, and 
Harry P. Clagett. October 1951. 30p. diagrs., 
photo., tab. (NACA RM L51H01) 



AN INVESTIGATION AT TRANSONIC SPEEDS OF 
THE EFFECTS OF THICKNESS RATIO AND OF 
THICKENED ROOT SECTIONS ON THE AERODY- 
NAMIC CHARACTERISTICS OF WINGS WITH 47° 
SWEEPBACK, ASPECT RATIO 3.5, AND TAPER 
RATIO 0.2 IN THE SLOTTED TEST SECTION OF 
THE LANGLEY 8-FOOT HIGH-SPEED TUNNEL. 
Ralph P. Bielat, Daniel E. Harrison, and Domenic A. 
Coppolino. October 1951. 38p. diagrs., photo., tab. 
(NACA RM L5 1104a) 



FLIGHT DETERMINATION OF THE DRAG AND 
LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A ROCKET -POWERED MODEL 
OF A 60° DELTA-WING AIRPLANE FROM MACH 
NUMBERS OF 0.75 TO 1.70. Grady L. Mltcham, 
Norman L. CrablU, and Joseph E. Stevens. 
November 1951. 44p. diagrs., photos., tab. 
(NACA RM L51I04) 



A WIND-TUNNEL INVESTIGATION OF THE STATIC 
STABILITY CHARACTERISTICS OF A 1/8-SCALE 
EJECTABLE PILOT -SEAT COMBINATION AT A 
MACH NUMBER OF 0.8. Fioravante Visconti and 
Robert J. Nuber. December 1951. 29p. diagrs., 
photos. (NACA RM L51H08) 



FREE -SPINNING TUNNEL INVESTIGATION OF A 
1/20-SCALE MODEL OF THE DOUGLAS X-3 ATR- 
PLANE. Burton E. Hultz. December 26, 1951. 
23p. diagrs., photos., tab. (NACA RM L51K12) 



AERODYNAMIC CHARACTERISTICS AT SUPER- 
SONIC SPEEDS OF A SERIES OF WING-BODY 
COMBINATIONS HAVING CAMBERED WINGS WITH 
AN ASPECT RATIO OF 3.5 AND A TAPER RATIO 
OF 0.2. EFFECTS OF SWEEP ANGLE AND THICK- 
NESS RATIO ON THE AERODYNAMIC CHARACTER- 
ISTICS IN PITCH AT M = 1.60. Ross B. Robinson 
and Cornelius Driver. January 1952. 27p. diagrs., 
photos., tabs. (NACA RM L51K16a) 



THE STATIC AND DYNAMIC LONGITUDINAL STA- 
BILITY CHARACTERISTICS OF SOME SUPERSONIC 
AIRCRAFT CONFIGURATIONS Jesse L. Mitchell. 
January 1952. 19p. diagrs. (NACA RM L52A10a) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR- ARC SECTIONS AND 40° SWEEPBACK. 
ESTIMATED DOWNWASH ANGLES DERIVED FROM 

PRESSURE MEASUREMENTS ON THE TAIL AT 
MACH NUMBERS OF 1.40 AND 1.59. Frederick C. 
Grant and John P. Gapcynskl. March 1952. 27p. 
diagrs., photos., tabs. (NACA RM L51L17) 



LIFT, DRAG, AND PITCHING MOMENT OF LOW- 
ASPECT-RATK) WINGS AT SUBSONIC AND SUPER- 
SONIC SPEEDS - TWISTED AND CAMBERED TRI- 
ANGULAR WING OF ASPECT RATIO 2 WITH NACA 
0005-63 THICKNESS DISTRIBUTION. John C . 
Heitmeyer and Robert B. Petersen. April 1952. 
20p. diagrs., tabs. (NACA RM A52B08) 



LONGITUDINAL STABILITY AND DRAG CHARAC- 
TERISTICS AT MACH NUMBERS FROM 0.75 TO 1.5 
OF AN AIRPLANE CONFIGURATION HAVING A 60° 
SWEPT WING OF ASPECT RATIO 2.24 AS OB- 
TAINED FROM ROCKET-PROPELLED MODELS. 
A. James Vitale, John C. McFall, Jr., and John D. 
Morrow. April 1952. 43p. diagrs., photos., tabs. 
(NACA RM L51K06) 



LONGITUDINAL AERODYNAMIC CHARACTERISTICS 
OF MODEL AIRPLANE CONFKXJRATfON EQUIPPED 
WITH A SCALED X-l AIRPLANE WING. James H. 
Parks. April 1952. 37p. diagrs. 
(NACA RM L5lLl0a) 



THE AERODYNAMIC CHARACTERISTICS OF A 
SUPERSONIC AIRCRAFT CONFIGURATION WITH A 
40° SWEPTBACK WING THROUGH A MACH NUM- 
BER RANGE FROM TO 2.4 AS OBTAINED FROM 
VARIOUS SOURCES. M. Leroy Spearman and Ross 
B. Robinson. April 1952. 50p. diagrs., photo., 
tab. (NACA RM L52A21) 



EXPERIMENTAL INVESTIGATION OF THE STATIC 
AERODYNAMIC AND DYNAMIC DAMPING- IN -ROLL 
CHARACTERISTICS OF AN 8-CM AIRCRAFT 
ROCKET WITH SOLID AND SLOTTED FINS. Robert 
S. Chubb. June 1952. ii, 43p. diagrs., photo. 
(NACA RM A52C04) 



A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE AERODYNAMIC CHARACTERISTICS OF THREE 
4-PERCENT -THICK WINGS OF SWEEPBACK 
ANGLES 10.8°, 35o, AND 47°, ASPECT RATIO 3.5, 
AND TAPER RATIO 0.2 IN COMBINATION WITH A 
BODY. Ralph P. Bielat. July 1952. 33p. diagrs., 
photos., tab. (NACA RM L52B08) 



135 



(1) AERODYNAMICS 



AERODYNAMIC CHARACTERISTICS AT SUPER- 
SONIC SPEEDS OF A SERIES OF WING-BODY COM- 
BINATIONS HAVING CAMBERED WINGS WITH AN 
ASPECT RATIO OF 3.5 AND A TAPER RATIO OF 
0.2. EFFECTS OF SWEEP ANGLE AND THICKKESS 
RATIO ON THE AERODYNAMIC CHARACTERISTICS 
IN PITCH AT M = 2.01. Ross B. Robinson. July 
1952. 27p. diagrs., photo., tabs. 
(NACA RM L52E09) 



PRELIMINARY INVESTIGATION OF THE LOW- 
AMPLITUDE DAMPING IN PITCH OF TAILLESS 
DELTA- AND SWEPT-WING CONFIGURATIONS AT 
MACH NUMBERS FROM 0.7 TO 1.35. Charles T. 
D'Aiutolo and Robert N. Parker. August 1952. 27p. 
diagrs., photos., tab. (NACA RM L52G09) 



A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF NACELLE SHAPE AND POSITION 
ON THE AERODYNAMIC CHARACTERISTICS OF 
TWO 47° SWEPT BACK WING-BODY CONFIGURA- 
TIONS. Ralph P. Bielat and Daniel E. Harrison. 
September 1952. 87p. diagrs., photos., tab. 
(NACA RM L52G02) 



EFFECTS OF WING ELASTICITY ON THE AERO- 
DYNAMIC CHARACTERISTICS OF A 45° 
SWEPTBACK-WING- FUSELAGE COMBINATION 
MEASURED IN THE LANGLEY 8-FOOT TRANSONIC 
TUNNEL. Robert S. Osborne and John P. Mugler, 
Jr. September 1952. 27p. diagrs., photos. 
(NACA RM L52G23) 



AN INVESTIGATION OF A 0.16-SCALE MODEL OF 
THE DOUGLAS X-3 AIRPLANE. TO DETERMINE 
MEANS OF IMPROVING THE LOW -SPEED LONGI- 
TUDINAL STABILITY AND CONTROL CHARACTER- 
ISTICS. John W. McKee and John M. Riebe. 
November 1952. 90p. diagrs., photos., tabs. 
(NACA RM L52H01) 



LOW-SPEED STATIC LONGITUDINAL AND LAT- 
ERAL STABILITY CHARACTERISTICS OF A MODEL 
WITH LEADING-EDGE CHORD-EXTENSIONS INCOR- 
PORATED ON A 40° SWEPTBACK CIRCULAR-ARC 
WING OF ASPECT RATIO 4 AND TAPER RATIO 0.50. 
Kenneth W. Goodson and Albert G. Few, Jr. 
November 1952. 46p. diagrs., photos., tab. 
(NACA RM L52I18) 



AERODYNAMIC CHARACTERISTICS EXTENDED TO 
HIGH ANGLES OF ATTACK AT TRANSONIC SPEEDS 
OF A SMALL-SCALE 0° SWEEP WING, 45° SWEPT- 
BACK WING, AND 60° DELTA WING. Harleth G. 
Wiley. November 1952. 26p. diagrs. 
(NACA RM L52I30) 



INVESTIGATION AT HIGH SUBSONIC SPEEDS OF 
BODIES MOUNTED FROM THE WING OF AN 
UNSWEPT-WING-FUSELAGE MODEL, INCLUDING 
MEASUREMENTS OF BODY LOADS. H. Norman 
Silvers and Thomas J. King, Jr. November 1952. 
37p. diagrs., photos., tabs. (NACA RM L52J08) 



EFFECT OF LEADING-EDGE CHORD -EXTENSIONS 
ON SUBSONIC AND TRANSONIC AERODYNAMIC 
CHARACTERISTICS OF THREE MODELS HAVING 
45° SWEPTBACK WINGS OF ASPECT RATIO 4. 
Kenneth W. Goodson and Albert G. Few, Jr. 
January 1953. 31p. diagrs., photos., tab. 
(NACA RM L52K21) 



LONGITUDINAL STABILITY, CONTROL EFFEC- 
TIVENESS, AND DRAG CHARACTERISTICS AT 
TRANSONIC SPEEDS OF A ROCKET -PROPELLED 
MODEL OF AN AIRPLANE CONFIGURATION 
HAVING AN UNSWEPT TAPERED WING OF ASPECT 
RATIO 3.0 AND NACA 65A004.5 AIRFOIL SECTIONS. 
JohnC. McFall, Jr., and James A. Hollinger. 
January 1953. 30p. diagrs., photos. 
(NACA RM L52L04) 



STABILITY OF BODIES OF REVOLUTION HAVING 
FINENESS RATIOS SMALLER THAN 1.0 AND 
HAVING ROUNDED FRONTS AND BLUNT BASES. 
Stanley H. Scher and James S. Bowman, Jr. 
January 1953. 23p. diagrs., tabs. 
(NACA RM L52L08) 



A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF BODY INDENTATION, AS SPEC- 
IFIED BY THE TRANSONIC DRAG-RISE RULE, ON 
THE AERODYNAMIC CHARACTERISTICS AND 
FLOW PHENOMENA OF A 45° SWEPTBACK-WING - 
BODY COMBINATION . Harold L . Robinson . 
February 1953. 33p. diagrs., photos., tab. 
(NACA RM L52L12) 



SOME MEASUREMENTS OF FLYING QUALITIES OF 
A DOUGLAS D-558-n RESEARCH AIRPLANE DUR- 
ING FLIGHTS TO SUPERSONIC SPEEDS. Herman O. 
Ankenbruck and Theodore E. Dahlen. March 1953. 
25p. diagrs., photos., tab. (NACA RM L53A06) 



SOME APPROXIMATE METHODS FOR ESTIMATING 
THE EFFECTS OF AEROELASTIC BENDING OF 
ROCKET -PROPELLED MODEL-BOOSTER COMBI- 
NATIONS. Richard G. Arbic, George White, and 
Warren Gillespie, Jr. March 1953. 40p. diagrs., 
photos., tabs. (NACA RM L53A08) 



WIND-TUNNEL INVESTIGATION OF A RAM -JET 
MISSILE MODEL HAVING A WING AND CANARD 
SURFACES OF DELTA PLAN FORM WITH 10° 
SWEPT LEADING EDGES. FORCE AND MOMENT 
CHARACTERISTICS OF VARIOUS COMBINATIONS 
OF COMPONENTS AT A MACH NUMBER OF 1.6. 
Clyde V- Hamilton, Cornelius Driver, and John R. 
Sevier, Jr. March 1953. 48p. diagrs., photo., 
tabs. (NACA RM L53A14) 



FLIGHT DETERMINATION OF THE LONGITUDINAL 
STABILITY IN ACCELERATED MANEUVERS AT 
TRANSONIC SPEEDS FOR THE DOUGLAS D- 558-11 
RESEARCH AIRPLANE INCLUDING THE EFFECTS 
OF AN OUTBOARD WING FENCE. Jack Flschel and 
Jack Nugent. March 1953. 28p. diagrs., photo., 
tab. (NACA RM L53A16) 



LIFT, DRAG, AND PITCHING MOMENT OF LOW- 
ASPECT-RATIO WINGS AT SUBSONIC AND SUPER- 
SONIC SPEEDS. Charles F. Hall. April 1953. 
132p. diagrs., tabs. (NACA RM A53A30) 



MEASUREMENTS OBTAINED DURING THE GLIDE- 
FLIGHT PROGRAM OF THE BELL X-2 RESEARCH 
AIRPLANE. Richard E. Day. July 30, 1953. 27p. 
diagrs., photos., tabs. (NACA RM L53G03a) 



136 



) AERODYNAMICS 



THE INFLUENCE OF A CHANGE IN BODY SHAPE 
ON THE EFFECTS OF TWIST AND CAMBER AS 
DETERMINED BY A TRANSONIC WIND-TUNNEL 
INVESTIGATION OF A 45° SWEPTBACK WING- 
FUSELAGE CONFIGURATION. Daniel E. Harrison. 
August 1953. 23p. diagrs., tab. 
(NACA RM L53B03) 



A ROCKET-MODEL INVESTIGATION OF THE LON- 
GITUDINAL STABILITY, LIFT, AND DRAG CHAR- 
ACTERISTICS OF THE DOUGLAS X-3 CONFIGURA- 
TION WITH HORIZONTAL TAIL OF ASPECT RATIO 
4.33. Robert F. Peck and James A. Hollinger. 
August 1953. 33p. diagrb., phuios. 
(NACA RM L53F19a) 



EFFECTS OF LEADING-EDGE SLATS ON THE 
AERODYNAMIC CHARACTERISTICS OF A 45° 
SWEPTBACK WING- FUSELAGE CONFIGURATION 
AT MACH NUMBERS OF 0.4 TO 1.03. Jack F. 

Runckel and Seymour Steinberg. August 1953. 50p. 
diagrs., photos. (NACA RM L53F23) 



A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECT OF MODIFICATIONS TO AN IN- 
DENTED BODY IN COMBINATION WITH A 45° 
SWEPTBACK WING. Donald L. Loving. September 
1953. 29p. diagrs., photos., tabs. 
(NACA RM L53F02) 



INVESTIGATION OF SPOILER AILERONS WITH AND 
WITHOUT A GAP BEHIND THE SPOILER ON A 45° 
SWEPTBACK WING-FUSELAGE COMBINATION AT 
MACH NUMBERS FROM 0.60 TO 1.03. F. E. West, 
Jr., William Solomon, and Edward M. Brummal. 
September 1953. 38p. diagrs. (NACA RM L53G07a) 



THEORETICAL CALCULATIONS OF THE STABILI- 
TY DERIVATIVES AT SUPERSONIC SPEEDS FOR A 
HIGH-SPEED AIRPLANE CONFIGURATION. 
Kenneth Margolis and Percy J. Bobbitt. October 
1953. 59p. diagrs., tab, (NACA RM L53G17) 



A FLIGHT INVESTIGATION AT MACH NUMBERS 
FROM 0.67 TO 1.81 OF THE LONGITUDINAL 
STABILITY AND CONTROL CHARACTERISTICS OF 
A 60° DELTA-WING MISSILE CONFIGURATION 
HAVING AN ALL-MOVABLE TAIL. Martin T. 
Moul and Hal T. Baber, Jr. October 1953. 43p. 
diagrs., photo. (NACA RM L53G29) 



INVESTIGATION OF THE EFFECT OF SPANWISE 
POSITIONING OF A VERTICALLY SYMMETRIC 
OGIVE -CYLINDER NACELLE ON THE HIGH-SPEED 
AERODYNAMIC CHARACTERISTICS OF A 45° 
SWEPTBACK TAPERED-IN-THTCKNESS WING OF 
ASPECT RATIO 6 WITH AND WITHOUT A FUSE- 
LAGE . H. Norman Silvers and Thomas J. King, Jr. 
October 1953. 62p. diagrs., tabs. 
(NACA RM L53H17) 



RELATIONSHIP OF FLOW OVER A 45° SWEPT- 
BACK WING WITH AND WITHOUT LEADING -EDGE 
CHORD-EXTENSIONS TO LONGITUDINAL STABIL- 
ITY CHARACTERISTICS AT MACH NUMBERS FROM 
0.60 TO 1.03. F. E. West. Jr . and James H. 
Henderson. October 1953. 47p. diagrs .. photos. 
(NACARM L53H18b) 



THE INTERPRETATION OF NONLINEAR PITCHING 
MOMENTS IN RELATION TO THE PITCH-UP 
PROBLEM. George S. Campbell and Joseph Weil. 
October 1953. 32p. diagrs., tabs. 
(NACA RM L53I02) 



PRELIMINARY INVESTIGATION OF THE EFFECTS 
OF SEVERAL SEEKER-NOSE CONFIGURATIONS ON 
THE LONGITUDINAL CHARACTERISTICS OF A 
CANARD-TYPE MISSILE AT A MACH NUMBER OF 
1.60. A. Warner Robins. October 1953. 25p. 
diagrs., photos., tabs. (NACA RM L53I18) 



LONGITUDINAL CHARACTERISTICS OF WINGS. 
Thomas A. Toll. October 1953. 18p. diagrs. 
(NACA RM L53I21b) 



THE EFFECT OF NOSE RADIUS AND SHAPE ON 
THE AERODYNAMIC CHARACTERISTICS OF A 
FUSELAGE AND A WING-FUSELAGE COMBINATION 
AT ANGLES OF ATTACK. John P. Gapcynski and 
A. Warner Robins. October 1953. 23p. diagrs. 
(NACA RM L53I23a) 



FLIGHT MEASUREMENTS OF THE HORIZONTAL- 
TAIL LOADS ON A SWEPT-WING FIGHTER AIR- 
PLANE AT TRANSONIC SPEEDS. Me Win Sadoff. 
November 1953. 58p. diagrs., photo., tab. 
(NACA RM A53G10) 



LOW-SPEED STATIC STABILITY AND CONTROL 
CHARACTERISTICS OF A 1/4-SCALE MODEL OF 
THE BELL X-l AIRPLANE EQUIPPED WITH A 
4-PERCENT -THICK, ASPECT-RATIO-4, UNSWEPT 
WING. William C. Moseley, Jr., and Robert T. 
Taylor. November 1953. 53p. diagrs., photos., 
tab. (NACA RM L53H27) 



STATIC LONGITUDINAL STABILITY AND CONTROL 
CHARACTERISTICS OF A 1/16-SCALE MODEL OF 
THE DOUGLAS D-558-H RESEARCH AIRPLANE AT 
MACH NUMBERS OF 1.61 AND 2.01. M. Leroy 
Spearman. November 1953. 34p. diagrs., tabs. 
(NACA RM L53I22) 



RECENT DESIGN STUDIES DIRECTED TOWARD 
ELIMINATION OF PITCH-UP. Joseph Weil and 
W. H. Gray. November 1953. 16p. diagrs., tab. 
(NACA RM L53I23c) 



A STUDY OF THE USE OF LEADING-EDGE 
NOTCHES AS A MEANS FOR IMPROVING THE LOW- 
SPEED PITCHING-MOMENT CHARACTERISTICS OF 
A THIN 450 SWEPT WING OF ASPECT RATIO 4. 
Joseph Weil and William D. Morrison, Jr. 
December 1953. 17p. diagrs. (NACARM L53j27a) 



EFFECT OF LARGE DEFLECTIONS OF A CANARD 
CONTROL AND DEFLECTIONS OF A WING-TD? 
CONTROL ON THE STATIC-STABILITY AND 
INDUCED-ROLL CHARACTERISTICS OF A CRUCI- 
FORM CANARD MISSILE AT A MACH NUMBER OF 
2.01. M. Leroy Spearman. December 1953. 20p. 
diagrs., tabs. (NACA RM L53K03) 



EFFECTS OF LEADING-EDGE CHORD EXTENSIONS 
AND AN ALL-MOVABLE HORIZONTAL TAIL ON 
THE AERODYNAMIC CHARACTERISTICS OF A 
WING-BODY COMBINATION EMPLOYING A TRI- 
ANGULAR WING OF ASPECT RATIO 3 MOUNTED IN 
A HIGH POSITION AT SUBSONIC AND SUPERSONIC 
SPEEDS. Benton E. Wetzel and Frank A. Pfyl. 
January 1954. 35p. diagrs., photo., tabs. 
(NACA RM A53J14a) 



137 



(1) AERODYNAMICS 



LONGITUDINAL STABILITY CHARACTERISTICS 
AT TRANSONIC SPEEDS OF A ROCKET - 
PROPELLED MODEL OF AN AIRPLANE CON- 
FIGURATION HAVING A 450 SWEPT WING OF 
ASPECT RATIO 6.0. John C. McFall, Jr. 
January 1954. 34p. diagrs., photos. 
(NACA RM L53G22a) 



DETERMINATION OF LONGITUDINAL STABILITY 
IN SUPERSONIC ACCELERATED MANEUVERS FOR 
THE DOUGLAS D-558-II RESEARCH AIRPLANE. 
Herman O. Ankenbruck. February 1954. 29p. 
diagrs., photos., tab. (NACA RM L53J20) 



EFFECT OF WING SLATS AND INBOARD WING 
FENCES ON THE LONGITUDINAL STABILITY 
CHARACTERISTICS OF THE DOUGLAS D-558-U 
RESEARCH AIRPLANE IN ACCELERATED MANEU- 
VERS AT SUBSONIC AND TRANSONIC SPEEDS. 
Jack Fischel. February 1954. 12 5p. diagrs., 
photos., tabs. (NACA RM L53L16) 



EFFECT OF NOSE SHAPE AND TRAILING -EDGE 
BLUNTNESS ON THE AERODYNAMIC CHARACTER- 
ISTICS OF AN UNSWEPT WING OF ASPECT RATIO 
3.1, TAPER RATIO 0.4, AND 3-PERCENT THICK- 
NESS. JohnC Heitmeyer. March 1954. 36p. 
diagrs., tabs. (NACA RM A54A04) 



AERODYNAMIC CHARACTERISTICS AT TRANSONIC 
AND SUPERSONIC SPEEDS OF A ROCKET- 
PROPELLED AIRPLANE CONFIGURATION HAVING 
A 52.50 DELTA WING AND A LOW, SWEPT HORI- 
ZONTAL TAIL- Alan B. Kehlet. March 1954. 31p. 
diagrs., photos. (NACA RM L54A20) 



AN ANALYSIS OF PRESSURE STUDIES AND EX- 
PERIMENTAL AND THEORETICAL DOWNWASH 
AND SIDEWASH BEHIND FIVE POINTED-TIP WINGS 
AT SUPERSONIC SPEEDS. William B. Boatright. 
April 1954. ii, 119p. diagrs., photos. 
(NACA RM L54B10) 



AERODYNAMIC CHARACTERISTICS OF A 
CRUCIFORM-WING MISSILE WITH CANARD CON- 
TROL SURFACES AND OF SOME VERY SMALL 
SPAN WING-BODY MISSILES AT A MACH NUMBER 
OF 1.41. M. Leroy Spearman and Ross B. 
Robinson. April 1954. 27p. diagrs.. tabs. 
(NACARML54B11) 



COMPARISON OF EXPERIMENTAL WITH CALCU- 
LATED RESULTS FOR THE LIFTING EFFECTIVE- 
NESS OF A FLEXIBLE 45° SWEPTBACK WING OF 
ASPECT RATIO 6.0 AT MACH NUMBERS FROM 0.8 
TO 1.3. Richard E. Walters. April 1954. 35p. 
diagrs., photos., tab. (NACA RM L54B16) 



INVESTIGATION AT HIGH SUBSONIC SPEEDS OF 
FINNED AND UNFINNED BODIES MOUNTED AT 
VARIOUS LOCATIONS FROM THE WINGS OF UN- 
SWEPT, AND SWEPT -WING-FUSELAGE MODELS, 
INCLUDING MEASUREMENTS OF BODY LOADS. 
William J. Alford, Jr., and H. Norman Silvers. 
April 1954. 93p. diagrs., photos., tabs. 
(NACA RM L54B18) 



ROCKET-POWERED MODEL INVESTIGATION OF 
LIFT, DRAG, AND STABILITY OF A BODY -TAIL 
CONFIGURATION AT MACH NUMBERS FROM 0.8 
TO 2.3 AND ANGLES OF ATTACK BETWEEN t6.5°. 
Warren Gillespie, Jr., and Albert E. Dietz. April 
1954. 42p. diagrs., photos., tabs. 
(NACA RM L54C04) 



INVESTIGATION AT HIGH SUBSONIC SPEEDS OF 
THE EFFECT OF ADDING VARIOUS COMBINATIONS 
OF MISSILES ON THE AERODYNAMIC CHARACTER- 
ISTICS OF SWEPTBACK AND UNSWEPT WINGS 
COMBINED WITH A FUSELAGE. H. Norman 
Silvers and William J. Alford, Jr. June 1954. 39p. 
diagrs., photo., tabs. (NACA RM L54D20) 



LOW -AMPLITUDE DAMPING-IN -PITCH CHARAC- 
TERISTICS OF TAILLESS DELTA -WING-BODY 
COMBINATIONS AT MACH NUMBERS FROM 0.80 
TO 1.35 AS OBTAINED WITH ROCKET-POWERED 
MODELS. Charles T. D'Aiutolo. June 1954. 34p. 
diagrs., photos., tab. (NACA RM L54D29) 



A WIND-TUNNEL INVESTIGATION OF THE USE 
OF SPOILERS FOR OBTAINING STATIC LONGITU- 
DINAL STABILITY OF A CANARD -MISSILE MODEL 
IN REVERSE FLIGHT. Herman S. Fletcher. June 
1954. 15p. diagrs., tab. (NACA RM L54E05) 



A FLIGHT INVESTIGATION AT TRANSONIC SPEEDS 
OF THE AERODYNAMIC CHARACTERISTICS OF A 
MODEL HAVING A THIN UNSWEPT WING OF 
ASPECT RATIO 3.1. Maurice D. White. August 
1954. 41p. diagrs., photo., tabs. 
(NACA RM A54E12) 



WIND-TUNNEL INVESTIGATION AT A MACH NUM- 
BER OF 2.01 OF THE AERODYNAMIC CHARACTER- 
ISTICS TN COMBINED PITCH AND SIDESLIP OF 
SOME CANARD-TYPE MISSILES HAVING CRUCI- 
FORM WINGS AND CANARD SURFACES WITH 70° 
DELTA PLAN FORMS. M. Leroy Spearman and 
Cornelius Driver. August 1954. 121p. diagrs., 
tabs. (NACA RM L54F09) 



INVESTIGATION OF THE EFFECT OF INDENTATION 
ON AN M-PLAN-FORM-WING-BODY COMBINATION 
AT TRANSONIC SPEEDS. Donald L. Loving. 
August 1954. 24p. diagrs., photos., tab. 
(NACA RM L54F14) 



EFFECTS OF CANOPY, REVISED VERTICAL TAIL, 
AND A YAW-DAMPER VANE ON THE AERODYNAM- 
IC CHARACTERISTICS OF A 1/16-SCALE MODEL 
OF THE DOUGLAS D-558-H RESEARCH AIRPLANE 
AT A MACH NUMBER OF 2.01. Ross B. Robinson. 
August 1954. 29p. diagrs., tabs. 
(NACA RM L54F25) 



AERODYNAMIC CHARACTERISTICS AT A MACH 
NUMBER OF 2.01 OF TWO CRUCIFORM MISSILE 
CONFIGURATIONS HAVING 70<> DELTA WINGS 
WITH LENGTH -DIAMETER RATIOS OF 14.8 AND 
17.7 WITH SEVERAL CANARD CONTROLS. 
M. Leroy Spearman and Ross B. Robinson. August 
1954. 32p. diagrs., tabs. (NACA RM L54G20) 



STABILITY AND DRAG CHARACTERISTICS AT 
MACH NUMBERS FROM 0.8 TO 1.5 OF A FREE- 
FLIGHT MODEL HAVING 3-PERCENT-THICK, 60<> 
TRIANGULAR WING AND HORIZONTAL TAIL SUR- 
FACES. Rowe Chapman, Jr., and Harvey A. 
Wallskog. August 1954. 3 Op. diagrs., photos., tab. 
(NACA RM L54G23a) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR -ARC SECTIONS AND 40° SWEEPBACK. 
STABILITY AND CONTROL CHARACTERISTICS AT 
A MACH NUMBER OF 1.61 OF THE COMPLETE 
CONFIGURATION EQUDPPED WITH SPOILERS. 
Clyde V. Hamilton and Cornelius Driver. September 
1954. 28p. diagrs. (NACA RM L54F15) 



138 



(1) AERODYNAMICS 



LOW-SPEED MEASUREMENT OF STATIC STABIL- 
ITY AND DAMPING DERIVATIVES OF A 60° 
DELTA-WING MODEL FOR ANGLES OF ATTACK 
OF 0O TO 90°. Donald E. Hewes. September 1954. 
30p. diagrs., photo., tab. (NACA RM L54G22a) 



AERODYNAMIC CHARACTERISTICS AT TRANSONIC 
AND SUPERSONIC SPEEDS OF A ROCKET- 
PROPELLED AIRPLANE CONFIGURATION HAVING 
A DIAMOND-PLAN-FORM WING OF ASPECT RATIO 
3.08 AND A LOW, SWEPT HORIZONTAL TAIL. 
Alan B. Kehlet. Septembef 1954. 37p. diagrs., 
photos. (NACA RM L54G27a^ 



LONGITUDINAL STABILITY CHARACTERISTICS IN 
ACCELERATED MANEUVERS AT SUBSONIC AND 
TRANSONIC SPEEDS OF THE DOUGLAS D-558-II 
RESEARCH AIRPLANE EQUIPPED WITH A 
LEADING-EDGE WING CHORD-EXTENSION. Jack 
Fischel and Cyril D. Brunn. October 1954. 62p. 
diagrs., photos., tab. (NACA RM H54H16) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR-ARC SECTIONS AND 40° SWEEPBACK. 
STATIC LONGITUDINAL AND LATERAL STABILITY 
AND CONTROL CHARACTERISTICS AT A MACH 
NUMBER OF 1.89. M. Leroy Spearman and Edward 
B. Palazzo. October 1954. 24p. diagrs., photo., 
tab. (NACA RM L54G26a) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR -ARC SECTIONS AND 40° SWEEPBACK. 
AERODYNAMIC CHARACTERISTICS OF THE CON- 
FIGURATION EQUIPPED WITH A CANARD CON- 
TROL SURFACE AT A MACH NUMBER OF 1.89. 
M. Leroy Spearman and Edward B. Palazzo. 
October 1954. 22p. diagrs., photo., tab. 
(NACA RM L54H19) 



DETERMINATION OF LONGITUDINAL HANDLING 
QUALITIES OF THE D-558-II RESEARCH AIRPLANE 
AT TRANSONIC AND SUPERSONIC SPEEDS TO A 
MACH NUMBER OF ABOUT 2.0. Herman O. 
Ankenbruck. November 1954. 25p. diagrs., photos., 
tab. (NACA RM H54G29a) 



LONGITUDINAL STABILITY CHARACTERISTICS AT 
TRANSONIC SPEEDS OF A CANARD CONFIGURA- 
TION HAVING A 45° SWEPTBACK WING OF ASPECT 
RATIO 6.0 AND NACA 65A009 AIRFOIL SECTION. 
A. James Vltale and John C. McFall, Jr. November 
1954. 24p. diagrs., photos., tab. 
(NACARM L54I01) 



LOW-AMPLITUDE DAMPING-IN -PITCH CHARAC- 
TERISTICS OF FOUR TAILLESS SWEPT WING- 
BODY COMBINATIONS AT MACH NUMBERS FROM 
0.85 TO 1.30 AS OBTAINED WITH ROCKET- 
POWERED MODELS. Charles T. D'Aiutolo. 
November 1954. 34p. diagrs., photos., tab. 
(NACA RM L54I10) 



LOW-SPEED MEASUREMENTS OF ROLLING AND 
YAWING STABILITY DERIVATIVES OF A 60° 
DELTA-WING MODEL. Joseph L. Johnson, Jr. 
December 1954. 17p. diagrs., tab. 
(NACA RM L54G27> 



PRELIMINARY LOW-SPEED WIND-TUNNEL INVES- 
TIGATION OF SOME ASPECTS OF THE AERODY- 
NAMIC PROBLEMS ASSOCIATED WITH MISSILES 
CARRIED EXTERNALLY IN POSITIONS NEAR AIR- 
PLANE WINGS. William J. Alford, Jr., H. Norman 
Silvers, and Thomas J. King, Jr. December 1954. 
30p. diagrs., photos., tab. (NACARM L54J20) 



A FLIGHT INVESTIGATION AT TRANSONIC 
SPEEDS AND SMALL ANGLES OF ATTACK OF THE 
AERODYNAMIC CHARACTERISTICS OF A MODEL 
HAVING A 450 SWEPTBACK WING OF ASPECT 
RATIO 3 WITH AN NACA 64A006 AIRFOIL SECTION. 
George H. Holdaway. January 1955. 32p. diagrs., 
photo., tab. (NACA RM A54I17) 



EFFECT OF TAPER RATIO ON LIFT, DRAG, AND 
PITCHING -MOMENT CHARACTERISTICS OF THIN 
WINGS OF ASPECT RATIO 3 WITH 53.1© SWEEP- 
BACK OF LEADING EDGE AT SUBSONIC AND 
SUPERSONIC SPEEDS. Benton E. Wetzel. 
January 1955. 25 p. diagrs., photo., tabs. 
(NACA RM A54J20) 



LONGITUDINAL STABILITY CHARACTERISTICS 
AT MACH NUMBERS UP TO 0.92 OF A WING- 
BODY- TAIL COMBINATION HAVING A WING WITH 
45° OF SWEEPBACK AND A TAIL IN VARIOUS 
VERTICAL POSITIONS. Jack D. Stephenson, 
Angel o Bandettini, and Ralph Selan. January 1955. 
64p. diagrs., photos., tabs. (NACA RM A54K09) 



JET EFFECTS ON LONGITUDINAL TRIM OF AN 
AIRPLANE CONFIGURATION MEASURED AT MACH 
NUMBERS BETWEEN 1.2 AND 1.8. Robert F. Peck. 
January 1955. 17p. diagrs., photos. 
(NACA RM L54J29a) 



TRANSONIC LONGITUDINAL AERODYNAMIC 
EFFECTS OF SWEEPING UP THE REAR OF THE 
FUSELAGE OF A ROCKET-PROPELLED AIR- 
PLANE MODEL HAVING NO HORIZONTAL TAIL. 
James H. Parks. January 1955. 3 Op. diagrs., 
photo. (NACA RM L54K12) 



FLIGHT EXPERIENCE WITH TWO HIGH-SPEED 
AIRPLANES HAVING VIOLENT LATERAL- 
LONGITUDINAL COUPLING IN AILERON ROLLS. 
NACA High-Speed Flight Station. February 1955. 
30p. diagrs., photos., tabs. (NACA RM H55A13) 



EFFECTS OF INCREASING REYNOLDS NUMBER 
FROM 2 x 106 TO 6 x 106 ON THE AERODYNAMIC 
CHARACTERISTICS AT TRANSONIC SPEEDS OF A 
450 SWEPT WING WITH 6° LEADING-EDGE DROOP. 
James W. Schmeer and J. Lawrence Cooper. 
February 1955. 22p. diagrs., photo. 
(NACA RM L54L10) 



THE LONGITUDINAL CHARACTERISTICS AT MACH 
NUMBERS UP TO 0.92 OF SEVERAL WING- 
FUSELAGE-TAIL COMBINATIONS HAVING SWEPT- 
BACK WINGS WITH NACA FOUR-DIGIT THICKNESS 
DISTRIBUTIONS. Fred B . Sutton and Jerald K. 
Dickson. March 1955. 128p. diagrs., photos., tab. 
(NACA RM A54L08) 



EFFECTS OF TAPER RATIO ON THE LONGITUDI- 
NAL CHARACTERISTICS AT MACH NUMBERS 
FROM 0.6 TO 1-4 OF A WING-BODY-TAIL COMBI- 
NATION HAVING AN UNSWEPT WING OF ASPECT 
RATIO 3. James L. Summers, Stuart L. Treon, 
and Lawrence A. Graham. March 1955. 45p. 
diagrs., photo. (NACA RM A54L20) 



A FLIGHT INVESTIGATION AT TRANSONIC SPEEDS 
OF A MODEL HAVING A TRIANGULAR WING OE?/ 
ASPECT RATIO 4. Loren G. Bright. March 1955. 
4 Op. diagrs., photos., tabs. (NACA RM A54L27) 



(1) AERODYNAMICS 



139 



EFFECTS OF SWEEP AND TAPER RATIO ON THE 
LONGITUDINAL CHARACTERISTICS OF AN ASPECT 
RATIO 3 WING -BODY COMBINATION AT MACH, 
NUMBERS FROM 0.6 TO 1.4. Earl D. Knech/ei and 
James L. Summers. March 1955. 36p. differs., 
photo. (NACA RM A55A03) 



EXPLORATORY INVESTIGATION OF THE LOW- 
SPEED STATIC STABILITY OF A CONFIGURATION 
EMPLOYING THREE IDENTICAL TRIANGULAR 
WING PANELS AND A BODY OF EQUAL LENGTH. 
Noel K. Delany. April 1955. 25p. diagrs .j photos. 
(NACA RM A55C28) 



A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE LONGITUDINAL FORCE AND MOMENT CHAR- 
ACTERISTICS OF TWO DELTA WINGS AND ONE 
CUPPED -TIP DELTA WING OF 4 PERCENT 
THICKNESS ON A SLENDER BODY . William E . 
Palmer and Dale L. Burrows. April 1955. 31p. 
diagrs., photo. (NACA RM L55A07a) 



LIFT, DRAG, AND LONGITUDINAL STABILITY AT 
MACH NUMBERS FROM 0.8 TO 2.1 OF A ROCKET - 
POWERED MODEL HAVING A TAPERED UNSWEPT 
WING OF ASPECT RATIO 3 AND INLINE TAIL 
SURFACES. Warren Gillespie, Jr. April 1955. 
29p. diagrs., photo., tabs. (NACA RM L55B10) 



COMPARISON OF THE STATIC STABILITY OF A 
68.7° DELTA- WING MODEL WITH DIHEDRAL AND 
A TWISTED AND CAMBERED WING MODEL OF THE 
SAME PLAN FORM. John W. Paulson. April 1955. 
18p. diagrs., tab. (NACA RM L55B11) 



INVESTIGATION OF THE EFFECTS OF AN AIRFOIL 
SECTION MODIFICATION ON THE AERODYNAMIC 
CHARACTERISTICS AT SUBSONIC AND SUPERSONIC 
SPEEDS OF A THIN SWEPT WING OF ASPECT 
RATIO 3 IN COMBINATION WITH A BODY. David 
Graham and William T. Evans. June 1955. 46p. 
diagrs., tabs. (NACA RM A55D11) 



A COMPARISON AT MACH NUMBERS UP TO 0.92 
OF THE CALCULATED AND EXPERIMENTAL 
DOWNWASH AND WAKE CHARACTERISTICS AT 
VARIOUS HORIZONTAL TAIL HEIGHTS BEHIND A 
WING WITH 45° OF SWEEPBACK. Jack D . 
Stephenson, Ralph Selan, and Angelo Bandettini. 
June 1955. 81p. diagrs., photos., tabs. 
(NACA RM A55D27a) 



ADDITIONAL MEASUREMENTS OF THE LOW- 
SPEED STATIC STABILITY OF A CONFIGURATION 
EMPLOYING THREE TRIANGULAR WING PANELS 
AND A BODY OF EQUAL LENGTH. Noel K. Delany. 
July 1955. 31p. diagrs. (NACA RM A55F02a) 



STABILITY AND CONTROL CHARACTERISTICS 
OBTAINED DURING DEMONSTRATION OF THE 
DOUGLAS X-3 RESEARCH AIRPLANE. Richard E. 
Day and Jack Fischel. July 1955. 51p. diagrs., 
photos., tab. (NACA RM H55E16) 



EFFECT OF SEVERAL WING MODIFICATIONS ON 
THE LOW-SPEED STALLING CHARACTERISTICS OF 
THE DOUGLAS D-558-U RESEARCH AIRPLANE. 
Jack Fischel and Donald Reisert. July 1955. 62p. 
diagrs., photos., tabs. (NACA RM H55E31a) 



INVESTIGATION AT HIGH SUBSONIC SPEEDS OF 
THE EFFECTS OF VARIOUS UNDERWING 
EXTERNAL-STORE ARRANGEMENTS ON THE 
AERODYNAMIC CHARACTERISTICS OF A 1/16- 
SCALE MODEL OF THE DOUGLAS D-558-II 
RESEARCH AIRPLANE. H. Norman Silvers and 
Thomas J. King, Jr. July 1955. 59p. diagrs., 
photos., tab. (NACA RM L55D11) 



INVESTIGATION OF THE EFFECTS OF BODY 
INDENTATION AND OF WING-PLAN-FORM 
MODIFICATION ON THE LONGITUDINAL CHARAC- 
TERISTICS OF A 60° SWEPT -WING-BODY COMBI- 
NATION AT MACH NUMBERS OF 1.41, 1.61, AND 
2.01. John R. Sevier, Jr. July 1955. 37p. diagrs,, 
tab. (NACA RM L55E17) 



SUMMARY AND ANALYSIS OF HORIZONTAL -TAIL 
CONTRIBUTION TO LONGITUDINAL STABILITY OF 
SWEPT -WING AIRPLANES AT LOW SPEEDS. 
Robert H. Neely and Roland F. Griner. August 1955. 
ii, 133p. diagrs., tabs. (NACA RM L55E23a) 



A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE STATIC LONGITUDINAL CHARACTERISTICS 
OF A 3-PERCENT-THICK, ASPECT-RATIO-3, 
DELTA WING CAMBERED AND TWISTED FOR HIGH 
LIFT -DRAG RATIOS. Dale L. Burrows and Warren 
A. Tucker. August 1955. 38p. diagrs., photos., 
tab. (NACA KM L55F02a) 



A FLIGHT INVESTIGATION AT TRANSONIC SPEEDS 
OF A MODEL HAVING A TRIANGULAR WING OF 
ASPECT RATIO 2. Maurice D. White. September 
1955. 39p. diagrs., photo., tabs. 
(NACA RM A55F21) 



AERODYNAMIC CHARACTERISTICS AT MACH NUM- 
BERS FROM 0.7 TO 1.75 OF A FOUR-ENGINE 
SWEPT-WING AIRPLANE CONFIGURATION AS 
OBTAINED FROM A ROCKET-PROPELLED MODEL 
TEST. Rowe Chapman, Jr. September i955. 39p. 
diagrs., photos., tabs. (NACA RM L55F23) 



LONGITUDINAL CHARACTERISTICS AT TRANSONIC 
AND SUPERSONIC SPEEDS OF A ROCKET- 
PROPELLED AIRPLANE MODEL HAVING A 60<> 
DELTA WING AND A LOW SWEPT HORIZONTAL 
TAIL. Robert F. Peck and Lucille C. Coltrane. 
September 1955. 33p. diagrs., photo., tabs. 
(NACA RM L55F27) 



FREE-FLIGHT INVESTIGATION TO OBTAIN DRAG- 
AT-LIFT AND STABILITY DATA FOR A 60° DELTA- 
WING-BODY CONFIGURATION OVER A MACH NUM- 
BER RANGE OF 1.3 TO 1.6. Clement J. Welsh. 
October 1955. 23p. diagrs., photo., tab. 
(NACA RM L55G14) 



EFFECTS OF LEADING-EDGE RADIUS ON THE 
LONGITUDINAL STABILITY OF TWO 45° SWEPT - 
BACK WINGS INCORPORATING LEADING-EDGE 
CAMBER AS INFLUENCED BY REYNOLDS NUM- 
BERS UP TO 8.00 x 10 6 AND MACH NUMBERS UP 
TO 0.290. Gerald V. Foster. October 1955. 44p. 
diagrs. (NACA RM L55H04) 



140 



(1) AERODYNAMICS 



A SYSTEMATIC STUDY OF THE EFFECTS OF 
LEADING-EDGE CHORD-EXTENSIONS ON THE 
LOW-SPEED LONGITUDINAL STABILITY CHARAC- 
TERISTICS OF THREE 45° SWEPTBACK WINGS. 
H. Neale Kelly. October 1955. 113p. diagrs., 
photo., tabs. (NACARM L55H19) 



EFFECT OF LEADING-EDGE SWEEPBACK ON LIFT, 
DRAG, AND PITCHING-MOMENT CHARACTERIS- 
TICS OF THIN WINGS OF ASPECT RATIO 3 AND 
TAPER RATIO 0.4 AT SUBSONIC AND SUPERSONIC 

SPEEDS. Benton E. Wetzel. November 1955. 22p. 
diagrs., tabs. (NACA RM A55H04a) 



WIND-TUNNEL INVESTIGATION AT TRANSONIC 
SPEEDS OF A JET CONTROL ON AN 80° DELTA- 
WING MISSILE. Thomas R. Turner and Raymond D. 

Vogler. November 1955. 32p. diagrs. 
(NACA RM L55H22) 



TRANSONIC WIND-TUNNEL INVESTIGATION OF 
THE EFFECTS OF EXTERNAL STORES AND STORE 
POSITION ON THE AERODYNAMIC CHARACTERIS- 
TICS OF A 1/16-SCALE MODEL OF THE DOUGLAS 
D-558-II RESEARCH AIRPLANE . Thomas C . Kelly . 
November 1955. 31p. diagrs., photos., tab. 
(NACA RM L55I07) 



INVESTIGATKW AT HIGH SUBSONIC SPEEDS OF 
THE STATIC LONGITUDINAL STABILITY CHARAC- 
TERISTICS OF A MODEL HAVING CROPPED-DELTA 
AND UNSWEPT WING PLAN FORMS AND SEVERAL 
TAIL CONFIGURATIONS. Albert G. Few, Jr. 
November 1955. 107p. diagrs., photo., tab. 
(NACA RM L 55123a) 



THE EFFECT OF LEADING -EDGE EXTENSIONS 
OF THE LONGITUDINAL CHARACTERISTICS AT 
MACH NUMBERS UP TO 0.92 OF A WING- 
FUSELAGE-TAIL COMBINATION HAVING A 40° 
SWEPTBACK WING WITH NACA 64A THICKNESS 
DISTRIBUTION. Fred B. Sutton. January 1956. 
52p. diagrs., photos., tabs. (NACA RM A55I29) 



EFFECT OF LARGE NEGATIVE DIHEDRAL OF THE 
HORIZONTAL TAIL ON LONGITUDINAL AND LAT- 
ERAL STABILITY CHARACTERISTICS OF A 
SWEPT -WING CONFIGURATION AT TRANSONIC 
SPEEDS. Donald D. Arabian. January 195fi. 24p. 
diagrs., photos. (NACA RM L55I20) 



AN INVESTIGATION OF THE AERODYNAMIC CHAR- 
ACTERISTICS AT TRANSONIC MACH NUMBERS OF 
A SWEPT -WING SUPERSONIC BOMBER CONFIGU- 
RATION. Ralph P. Bielat and J. Lawrence Cooper. 
February 1956. 92p. diagrs., photos., tabs. 
(NACA RM L53F05) 



SOME EFFECTS OF SWEEP AND THICKNESS ON 
THE EXPERIMENTAL DOWNWASH CHARACTER- 
ISTICS AT TRANSONIC SPEEDS OF A SERIES OF 
HIGHLY TAPERED WINGS WITH AN ASPECT RATIO 
OF 3 . TRANSONIC -BUMP METHOD . Albert G . 
Few, Jr. February 1956. 65p. diagrs., photo. 
(NACA RM L5?J12) 



PRELIMINARY FREE-FLIGHT STUDY OF THE 
DRAG AND STABILITY OF A SERIES OF SHORT- 
SPAN MISSILES AT MACH NUMBERS FROM 0.9 TO 
1.3. James Rudyard Hall. February 1956. 14p. 
diagrs., photo. (NACA RM L55J13) 



WIND-TUNNEL INVESTIGATION AT HIGH SUBSONIC 
SPEEDS OF SOME EFFECTS OF FUSELAGE CROSS- 
SECTION SHAPE AND WING HEIGHT ON THE STAT- 
IC LONGITUDINAL AND LATERAL STABILITY 
CHARACTERISTICS OF A MODEL HAVING A 45° 
SWEPT WING. Thomas J. King, Jr. February 
1956. 61p. diagrs., photo. (NACA RM L55J25) 



WIND-TUNNEL INVESTIGATION AT TRANSONIC 
SPEEDS OF A JET CONTROL ON A 35° SWEPT 
WING. TRANSONIC-BUMP METHOD. Raymond D. 
Vogler and Thomas R. Turner. February 1956. 
17p. diagrs. (NACA RM L55K09) 



LONGITUDINAL STABILITY INVESTIGATION FOR 
A MACH NUMBER RANGE OF 0.8 TO 1.7 OF AN 
AIRPLANE CONFIGURATION WITH A 45<> SWEPT 
WING AND A LOW HORIZONTAL TAIL. John C . 
McFall, Jr. February 1956. 32p. diagrs., photos:, 
tab. (NACA RM L55L09) 



RESULTS OF ROCKET MODEL TEST OF AN AIR- 
PLANE CONFIGURATION HAVING AN ARROW WING 
AND SLENDER FLAT -SIDED FUSELAGE. LOT, 
DRAG, LONGITUDINAL STABILITY, LATERAL 
FORCE, AND JET EFFECTS AT MACH NUMBERS 
BETWEEN 1 .0 AND 2.3. Robert F. Peck. 
February 1956. 26p. diagrs., photo. 
(NACA RM L55L29) 



SOME EFFECTS OF AILERONS ON THE VARIATION 
OF AERODYNAMIC CHARACTERISTICS WITH SIDE- 
SLXP AT LOW SPEED. Kenneth W. Goodson. 
March 1956. 40p. diagrs., tab. (NACA RM L55L20) 



LOW -SPEED STATIC STABILITY CHARACTERIS- 
TICS OF A CAMBERED-DELTA-WING MODEL. 
John M. Riebe and William C Moseley, Jr. March 
1956. 27p. diagrs. (NACA RM L55L21a) 



EFFECTS OF LEADING-EDGE RADIUS ON THE 
LONGITUDINAL STABILITY CHARACTERISTICS OF 
TWO 60° SWEPTBACK WINGS AT HIGH REYNOLDS 
NUMBERS. William C Schneider. March 1956. 
46p. diagrs. (NACA RM L55L30) 



FLIGHT MEASUREMENTS OF HORIZONTAL -TAIL 
LOADS ON THE DOUGLAS X-3 RESEARCH AIR- 
PLANE. Harriet J. Stephenson. April 1956. 33p. 
diagrs., photo., tab. (NACA RM H56A23> 



LOW-SPEED INVESTIGATION OF THE EFFECTS 
OF WING DIHEDRAL ANGLE AND FIN LENGTH ON 
THE STATIC STABILITY CHARACTERISTICS OF A 
MODEL HAVING AN 82° DELTA WING. Kenneth P. 
Spreemann. April 1956. 30p. diagrs. 
(NACA RM L55L30a) 



AN EXPERIMENTAL STUDY AT HIGH SUBSONIC 
SPEEDS OF SEVERAL TADL CONFKSURATIONS ON 
A MODEL WITH AN UNSWEPT WING. William C. 
Sleeman, Jr. April 1956. 67p. diagrs., photos. 
(NACA RM L56A06a) 



(1) AERODYNAMICS 



141 



LATERAL STABILITY CHARACTERISTICS BE- 
TWEEN MACH NUMBERS OF 0.80 AND 1.57 AND 
SIMULATION OF COUPLED MOTION AT MACH 
NUMBER 1.30 OF A ROCKET-PROPELLED MODEL 
OF AN AIRPLANE CONFIGURATION HAVING THIN 
HIGHLY TAPERED 45° SWEPTBACK SURFACES. 
Charles T. D'Alutolo and Allen B. Henning. April 
1956. 41p. diagrs., photos., tabs. 
(NACA RM L56A17) 



A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
STORE AND HORIZONTAL -TAIL LOADS AND SOME 
EFFECTS OF FUSELAGE -AFTERBODY MODIFICA- 
TIONS ON A SWEPT-WING FIGHTER AIRPLANE. 
Joseph M. Hallissy, Jr., and Louis Kudlac Ik. April 
1956. 79p. diagrs., photos. (NACA RM L56A26) 



LOW-SPEED MEASUREMENTS OF STATIC STABIL- 
ITY, DAMPING IN YAW, AND DAMPING IN ROLL 
OF A DELTA, A SWEPT, AND AN UNSWEPT WING 
FOR ANGLES OF ATTACK FROM 00 TO 90°. 
Joseph L. Johnson, Jr. April 1956. 19p. diagrs., 
tabs. (NACA RM L56B01) 



INVESTIGATION AT HIGH SUBSONIC SPEEDS OF 
THE EFFECT OF HORIZONTAL -TAIL LOCATION 
ON LONGITUDINAL AND LATERAL STABILITY 
CHARACTERISTICS OF A COMPLETE MODEL 
HAVING A SWEPTBACK WING IN A HIGH LOCA- 
TION. H. Norman Silvers and Thomas J. King, Jr. 
April 1956. 46p. diagrs., tab. (NACA RM L56B10) 



EFFECTS OF REYNOLDS NUMBER AND LEADING- 
EDGE SHAPE ON THE LOW-SPEED LONGITUDINAL 
STABILITY OF A 6-PERCENT-THICK 45<> SWEPT- 
BACK WING. William C. Schneider. April 1956 
32p. diagrs. (NACA RM L56B14) 



WIND-TUNNEL INVESTIGATION OF A RAM-JET 
MISSILE MODEL HAVING A WING AND CANARD 
SURFACES OF DELTA PLAN FORM WITH 70° 
SWEPT LEADING EDGES. FORCE AND MOMENT 
CHARACTERISTICS AT COMBINED ANGLES OF 
PITCH AND SIDESLIP FOR MACH NUMBER 2.01. 
Cornelius Driver and Clyde V. Hamilton. April 
1956. 67p. diagrs., photo., tabs. 
(NACA RM L56B21) 



FULL-SCALE WIND-TUNNEL TESTS OF THE LON- 
GITUDINAL STABILITY AND CONTROL CHARAC- 
TERISTICS OF THE XV- 1 CONVERTIPLANE IN THE 
AUTOROTATING FLIGHT RANGE. David H. Hickey. 
May 1956. 64p. diagrs., photos., tabs. 
(NACA RM A55K21a) 



A HORIZONTAL -TAIL ARRANGEMENT FOR 
COUNTERACTING STATIC LONGITUDINAL 
INSTABILITY OF SWEPTBACK WINGS. George G. 
Edwards and Howard F. Savage. May 1956. 51p. 
diagrs., photos., tab. (NACA RM A56D06) 



EFFECT OF AIRPLANE CONFIGURATION ON 
STATIC STABILITY AT SUBSONIC AND TRANSONIC 
SPEEDS. Edward C. Polhamus and Joseph M. 
Hallissy, Jr. May 1956. 17p. diagrs. 
(NACA RM L56A09a) 



EFFECT OF WING CAMBER AND TWIST AT MACH 
NUMBERS FROM 1.4 TO 2.1 ON THE LIFT, DRAG, 
AND LONGITUDINAL STABILITY OF A ROCKET- 
POWERED MODEL HAVING A 52.5° SWEPTBACK 
WING OF ASPECT RATIO 3 AND RJLINE TAIL SUR- 
FACES. Warren GiUesple, Jr. May 1956. 29p. 
diagrs . , photos . , tabs . (NACA RM L 56C 16) 



INVESTIGATION OF THE USE OF AREA SUCTION 
TO INCREASE THE EFFECTIVENESS OF 
TRAILING-EDGE FLAPS OF VARIOUS SPANS ON 
A WING OF 45° SWEEPBACK AND ASPECT RATIO 
6. Roy N. Griffin, Jr., and David H. Hickey. 
June 1956. 64p. diagrs., photo., tabs. 
(NACA RM A56B27) 



EFFECT OF SEVERAL WING MODIFICATIONS ON 
THE SUBSONIC AND TRANSONIC LONGITUDINAL 
HANDLING QUALITIES OF THE DOUGLAS D-558-II 
RESEARCH AIRPLANE . Jack Fischel and Donald 
Reisert. June 1956. 57p. diagrs., photos., tabs. 
{NACA RM H56C30) 



THE EFFECT OF CONICAL CAMBER ON THE 
STATIC LONGITUDINAL, LATERAL, AND DIREC- 
TIONAL CHARACTERISTICS OF A 45° SWEPTBACK 
WING AT MACH NUMBERS UP TO 0.96. Robert I. 
Sammonds and Robert M. Reynolds. July 1956. 
64p. diagrs., tabs. (NACA RM A56D02) 



THE USE OF AREA SUCTION FOR THE PURPOSE 
OF IMPROVING THE LONGITUDINAL CHARACTER- 
ISTICS OF A THIN UNSWEPT-WING MODEL 
EQUIPPED WITH LEADING- AND TRAILING-EDGE 
FLAPS. David G. Koenig. July 1956. 52p. 
diagrs., photo., tabs. (NACA RM A56D23} 



LOW -SPEED WIND-TUNNEL RESULTS FOR A THIN 
ASPECT-RATIO-1.85 POINTED-WING-FUSELAGE 
MODEL WITH DOUBLE SLOTTED FLAPS. Albert 
E. Brown. July 1956. 31p. diagrs., tabs. 
(NACA RM L56D03) 



BLOWING OVER THE FLAPS AND WING LEADING 
EDGE OF A THIN 49° SWEPT WING-BODY -TAIL 
CONFIGURATION IN COMBINATION WITH LEADING- 
EDGE DEVICES. H. Clyde McLemore and Marvin P. 
Fink. July 1956. 57p. diagrs., photo. 
(NACA RM L56E16) 



WIND-TUNNEL INVESTIGATION OF THE EFFECTS 
OF WING THICKNESS ON THE STATIC LONGITU- 
DINAL AND LATERAL STABILITY OF UNSWEPT 
WINGS OF ASPECT RATIO 3 AT HIGH SUBSONIC 
SPEEDS. William C. Hayes, Jr., and Edward C. 
Polhamus. August 1956. 43p. diagrs., photos. 
(NACA RM L56E30a) 



APPLICATION OF AREA SUCTION TO LEADING- 
EDGE AND TRAILING-EDGE FLAPS ON A 44° 
SWEPT-WING MODEL. Curt A. Holzhauser, Robert 
K. Martin, and V. Robert Page. September 1956, 
66p. diagrs., photos., tabs. (NACA RM A56F01) 



INVESTIGATION OF SPOILER-SLOT-DEFLECTOR 
AILERONS AND OTHER SPOILER AILERONS ON A 
45° SWEPTBACK-WING- FUSELAGE COMBINATION 
AT MACH NUMBERS FROM 0.60 TO 1.03. F. E. 
West, Jr., Charles F- Whitcomb, and James W 
Schmeer. September 1956. 59p, diagrs., tab. 
(NACA RM L56F15) 



TRANSONIC WmD-TUNNEL INVESTIGATION OF 
STATIC LONGITUDINAL FORCE AND MOMENT- 
CHARACTERISTICS OF TWO WING-BODY COMBI- 
NATIONS WITH CLIPPED-TD? AND FULL DELTA 
WINGS OF ASPECT RATIO 1.73. Dale L. Burrows. 
September 1956. 26p. diagrs. (NACA RM L56F21) 



142 



(1) AERODYNAMICS 



EFFECT OF A FUSELAGE ON THE LOW-SPEED 
LONGITUDINAL AERODYNAMIC CHARACTERISTICS 
OF A 45° SWEPTBACK WING WITH DOUBLE 
SLOTTED FLAPS. Rodger L. Naeseth. September 
1956. 31p. diagrs., tabs, (NACA RM L56G02) 



FREE-FLIGHT INVESTIGATION OVER A MACH 
NUMBER RANGE FROM 0.74 TO 1.43 AT LIFT CO- 
EFFICIENTS FROM -0.15 TO 0.75 OF AN AIRPLANE- 
CONFIGURATION MODEL HAVING A 52.5<> DELTA 
WING AND A LOW SWEPT HORIZONTAL TAIL. 
Alan B. Kehlet. September 1956. 41p. diagrs., 
photos. (NACA RM L56G09) 



STATIC STABILITY CHARACTERISTICS OF A 
CAMBERED-DELTA-WING MODEL AT HIGH 
SUBSONIC SPEEDS. William C. Moseley, Jr. 
October 1956. 35 p. diagrs., photos. 
(NACA RM L56H13) 



COMBINED EFFECTS OF WING TAPER RATIO AND 
LOW HORIZONTAL-TAIL POSITION ON LONGITU- 
DINAL STABILITY OF A 45° SWEPTBACK WING- 
BODY COMBINATION AT TRANSONIC SPEEDS. 
Stanley H. Spooner. October 1956. 28p. diagrs., 
tab. (NACA RM L56H24) 



A LOW -SPEED INVESTIGATION OF A HIGH-LIFT 
LATERAL-CONTROL DEVICE CONSISTING OF A 
SPOILER-SLOT-DEFLECTOR AND A TRAILING- 
EDGE FLAP ON A TAPERED 45° SWEPTBACK 
WING. Alexander D. Hammond and Jarrett K. 
Huffman. October 1956. 21p. diagrs. 
(NACA RM L56H31) 



LARGE-SCALE WIND-TUNNEL TESTS OF AN AIR- 
PLANE MODEL WITH A 450 SWEPTBACK WING OF 
ASPECT RATIO 2.8 WITH AREA SUCTION APPLIED 
TO TRAILING-EDGE FLAPS AND WITH SEVERAL 
WING LEADING-EDGE MODIFICATIONS. David G. 
Koenig and Kiyoahi Aoyagi. November 1956. 66p. 
diagrs., photo., tabs. (NACA RM A56H08) 



LOW -SPEED PRESSURE-DISTRIBUTION INVESTI- 
GATION OF A THIN-DELTA-WING-FUSELAGE 
MODEL WITH DOUBLE SLOTTED FLAP, EX- 
TENDED DOUBLE SLOTTED FLAP, AND CANARD. 
Deiwin R. Croom and Jarrett K. Huffman. November 
1956. 104 p. diagrs., tabs. (NACA RM L56I11) 



LOW -SPEED MEASUREMENT OF TAIL CONTRI- 
BUTION TO ROLLING STABILITY DERIVATIVES 
AND AIR-FLOW ANGULARITY AT THE TAIL FOR 
AN X-TAIL MODEL IN STEADY ROLL INCLUDING 
SOME EFFECTS OF WING-TIP STORES. Donald R. 
Riley. November 1956. 28p. diagrs., photo., tab. 
(NACA RM L56I21) 



FORCE TEST RESULTS FOR BODY-MOUNTED 
LATERAL CONTROLS AND SPEED BRAKES ON A 
45° SWEPT-WING MODEL AT MACH NUMBERS 
FROM 0.80 TO 0.98. F. E. West, Jr., and Chris C. 
Critzos. December 1956. 32p. diagrs., photos., 
tab. (NACA RM L56I05) 



AN ANALYSIS OF THE EFFECTS OF AEROELAS- 
TICITY ON STATIC LONGITUDINAL STABILITY 
AND CONTROL OF A SWEPT-WING AIRPLANE. 
Richard B. Skoog. 1957. ii, 12p. diagrs. 
(NACARept. 1298. Supersedes RM A51C19) 



A SECOND-ORDER SHOCK- EXPANSION METHOD 
APPLICABLE TO BODIES OF REVOLUTION NEAR 
ZERO LIFT. Clarence A. Syvertson and David H. 
Dennis. 1957. 11, 20 p. diagrs., tabs. 
(NACA Rept. 1328. Supersedes TN 3527) 



DETERMINATION OF LONGITUDINAL STABILITY 
AND CONTROL CHARACTERISTICS FROM FREE- 
FLIGHT MODEL TESTS WITH RESULTS AT TRAN- 
SONIC SPEEDS FOR THREE AIRPLANE CONFIGU- 
RATIONS. Clarence L. GiUis and Jesse L. Mitchell. 
1957. 11, 28p. diagrs., photos., tabs. 
(NACARept. 1337) 



A SUMMARY AND ANALYSIS OF THE LOW -SPEED 
LONGITUDINAL CHARACTERISTICS OF SWEPT: 
WINGS AT HIGH REYNOLDS NUMBER. G. Chester 
Furlong and James G. McHugh. 1957. ill, 149p. 
diagrs., tabs. (NACA Rept. 1339. Supersedes 
RM L52Dlftt 



INVESTIGATION OF DOWNWASH, SIDEWASH, AND 
MACH NUMBER DISTRIBUTION BEHIND A RECTAN- 
GULAR WING AT A MACH NUMBER OF 2.41. 3 
David Adamson and William B. Boat right. 1957. 
ii, 57p. diagrs., photos., tab. (NACARept. 1340. 
Supersedes RM L50G12) 



WIND-TUNNEL INVESTIGATION OF THE AERODY- 
NAMIC CHARACTERISTICS OF A SERIES OF 
SWEPT, HIGHLY TAPERED, THIN WINGS AT 
TRANSONIC SPEEDS. TRANSONIC -BUMP METHOD. 
Albert G. Few, Jr., and Paul G. Fournier. January 
1957. 57p. diagrs., photo. (NACA RM L56I24) 



STATIC LONGITUDINAL CHARACTERISTICS AT 
HIGH SUBSONIC SPEEDS OF A COMPLETE AIR- 
PLANE MODEL WITH A HIGHLY TAPERED WING 
HAVING THE 0.80 CHORD LINE UNSWEPT AND 
WITH SEVERAL TAIL CONFIGURATIONS. Kenneth 
W. Goodson. January 1957. 57p. diagrs., photo., 
tabs. (NACA RM L56J03) 



HIGH-PRESSURE BLOWING OVER FLAP AND WING 
LEADING EDGE OF A THIN LARGE-SCALE 49° 
SWEPT WING-BODY-TAIL CONFIGURATION IN 
COMBINATION WITH A DROOPED NOSE AND A 
NOSE WITH A RADIUS INCREASE. Marvin P. Fink 
andH. Clyde McLemore. May 1957. 40p. diagrs., 
photo. (NACA RM L57D23) 



THE SUBSONIC STATIC AERODYNAMIC CHARAC- 
TERISTICS OF AN AIRPLANE MODEL HAVING A 
TRIANGULAR WING OF ASPECT RATIO 3. I - EF- 
FECTS OF HORIZONTAL-TAB, LOCATION AND 
SIZE ON THE LONGmjDINAL CHARACTERISTICS. 
Bruce E. Tinling and Armando E. Lopez. July 1957. 
85p. diagrs., photo., tabs. (NACA TN 4041. Super- 
sedes RM A53L1 5) 



THE SUBSONIC STATIC AERODYNAMIC CHARAC- 
TERISTICS OF AN AIRPLANE MODEL HAVING A 
TRIANGULAR WING OF ASPECT RATIO 3. 
m - EFFECTS OF TRAILING-EDGE FLAPS. Bruce 
E. Tinling and A. V. Karpen. July 1957. 37p. 
diagrs., photos., tabs. (NACA TN 4043. Super- 
sedes RM A54L07) 



143 



(1) AERODYNAMICS 



GROUND EFFECTS ON THE LONGITUDINAL CHAR- 
ACTERISTICS OF TWO MODELS WITH WINGS 
HAVING LOW ASPECT RATIO AND POINTED TD?S. 
Donald A. Buell and Bruce E . Tlnllng. July 1957. 
48p. diagrs., photos., tabs. (NACA TN 4044. 
Supersedes RM A55E04) 



STATIC LONGITUDINAL AND LATERAL STABILITY 
CHARACTERISTICS AT LOW SPEED OF 45° 
SWEPTBACK-MIDWING MODELS HAVING WINGS 
WITH AN ASPECT RATIO OF 2, 4, OR 6. David F. 
Thomas, Jr., and Walter D. Wolhart. September 
1957. 30p. diagrs., photos., tabs. (NACA TN 4077) 



EXPERIMENTAL INVESTIGATION OF LIFT, DRAG, 
AND PITCHING MOMENT OF FIVE ANNULAR AIR- 
FOILS. Herman S. Fletcher. October 1957. 
25p. diagrs., photos. (NACA TN 4117) 



EFFECT OF GROUND PROXIMITY ON THE AERO- 
DYNAMIC CHARACTERISTICS OF A FOUR-ENGINE 
VERTICAL -TAKE -OFF -AND -LANDING 
TRANSPORT -AIRPLANE MODEL WITH TILTING 
WING AND PROPELLERS. William A. Newsom, 
Jr. October 1957, 15p. diagrs., photo., tab. 
(NACA TN4124) 



THE USE OF A LEADING-EDGE AREA-SUCTION 
FLAP AND LEADING- EDGE MODIFICATIONS TO 
IMPROVE THE HIGH-LIFT CHARACTERISTICS OF 
AN AIRPLANE MODEL WITH A WING OF 45° 
SWEEP AND ASPECT RATIO 2.8. David G. Koenig 
and Kiyoshi Aoyagi. November 1957. 46p. diagrs., 
photo., tabs. (NACA RM A57H21) 



INVESTIGATION OF DEFLECTORS AS GUST ALLE- 
VIATORS ON A 0.09-SCALE MODEL OF THE BELL 
X-5 AIRPLANE WITH VARIOUS WING SWEEP 
ANGLES FROM 20° TO 60<> AT MACH NUMBERS 
FROM 0.40 TO 0.90. Delwin R. Croom and Jarrett 
K. Huffman. November 1957. 28p. diagrs. 
(NACA TN 4175) 



INVESTIGATION OF THE EFFECTS OF PRO- 
PELLER DIAMETER ON THE ABILITY OF A 
FLAPPED WING, WITH AND WITHOUT 
BOUNDARY- LAYER CONTROL, TO DEFLECT A 
PROPELLER SLIPSTREAM DOWNWARD FOR 
VERTICAL TAKE-OFF. Kenneth P. Spreemann. 
December 1957. 47p. diagrs., photos. 
(NACA TN4181) 



THREE-DEGREE-OF-FREEDOM EVALUATION 
OF THE LONGITUDINAL TRANSFER FUNCTIONS 
OF A SUPERSONIC CANARD MISSILE CONFIGU- 
RATION INCLUDING CHANGES IN FORWARD 
SPEED. Ernest C. Seaberg. December 1957. 
29p. diagrs., photo., tabs. (NACA TN 4192. 
Supersedes RM L54C02) 



LOW-SPEED BOUNDARY-LAYER-CONTROL 
INVESTIGATION ON A THIN RECTANGULAR SEMI- 
SPAN WING WITH LEADING-EDGE AND TRAILING- 
EDGE FLAPS. Delwin R. Croom and Thomas R. 
Turner. January 1958. 213p. diagrs., tabs. 
(NACA RM L57J15) 



EFFECT OF FLOW INCIDENCE AND REYNOLDS 
NUMBER ON LOW-SPEED AERODYNAMIC CHAR- 
ACTERISTICS OF SEVERAL NONCIRCULAR CYL- 
INDERS WITH APPLICATIONS TO DIRECTIONAL 
STABILITY AND SPINNING. Edward C. Polhamus. 
January 1958. 54p. diagrs., photo., tab. 
(NACA TN 4176) 



WIND-TUNNEL INVESTIGATION OF THE STATIC 
LONGITUDINAL STABILITY AND TRIM CHARAC- 
TERISTICS OF A SWEPTBACK-WING JET- 
TRANSPORT MODEL EQUIPPED WITH AN 
EXTERNAL-FLOW JET-AUGMENTED FLAP. 
Joseph L. Johnson, Jr. January 1958. 89p. 
diagrs., tab. (NACA TN 4177) 



EFFECTIVENESS OF BOUNDARY-LAYER CON- 
TROL, OBTAINED BY BLOWING OVER A PLAIN 
REAR FLAP IN COMBINATION WITH A FORWARD 
SLOTTED FLAP, IN DEFLECTING A SLIPSTREAM 
DOWNWARD FOR VERTICAL TAKE-OFF. 
Kenneth P. Spreemann. February 1958. 32p. 
diagrs., photo. (NACA TN 4200) 



LOW-SUBSONIC INVESTIGATION TO DETERMINE 
THE CHORDW1SE PRESSURE DISTRIBUTION AND 
EFFECTIVENESS OF SPOILERS ON A THIN, LOW- 
ASPECT -RATIO, UNSWEPT, UNTAPERED, SEMI- 
SPAN WING AND ON THE WING WITH LEADING- 
AND TRAILING-EDGE FLAPS. Delwin R. Croom. 
April 1958. 133p. diagrs., tabs. 
(NACA RM L58B05) 



EFFECTS OF FIXING BOUNDARY-LAYER TRANSI- 
TION FOR AN UNSWEPT -WING MODEL AND AN 
EVALUATION OF POROUS TUNNEL-WALL INTER- 
FERENCE FOR MACH NUMBERS FROM 0.60 TO 
1.40. Louis S. Stivers, Jr., and Garth W. Lippmann. 
A P i -il 1958. 37p. diagrs. (NACA TN 1228) 



DATA FROM FLOW-FIELD SURVEYS BEHIND A 
LARGE-SCALE THIN STRAIGHT WING OF ASPECT 
RATIO 3. William T. Evans. June 1958. 13p. 
diagrs. (NACA RM A58D17) 



USE OF THE COANDA EFFECT FOR OBTAINING 
JET DEFLECTION AND LIFT WITH A SINGLE 
FLAT -PLATE DEFLECTION SURFACE. Uwe H. 
von Glahn. June 1958. 49p. diagrs., tabs. 
(NACA TN 4272) 



AERODYNAMIC RESEARCH ON FUSELAGES WITH 
RECTANGULAR CROSS SECTION. (Aerodynamische 
Untersuchungen an Rlimpfen mit rechteckahnlichem 
Querschnitt.) K. Maruhn. July 1958. 37p. diagrs. 
(NACA TM 1414. Translation from Jahrbuch 1942 
der deutschen Luftfahrtforschung, p. 263-279.) 



DYNAMIC STABILITY OF VEHICLES TRAVERSING 
ASCENDING OR DESCENDING PATHS THROUGH 
THE ATMOSPHERE. Murray Tobak and H. Julian 

Allen. July 1958. (i), 35p. diagrs. 
(NACA TN 4275) 



EFFECTS OF FIXING TRANSITION ON THE TRAN- 
SONIC AERODYNAMIC CHARACTERISTICS OF A 
WING -BODY CONFIGURATION AT REYNOLDS NUM- 
BERS FROM 2.4 TO 12 MILLION. Lynn W. Hunton. 
July 1958. 56p. diagrs. (NACA TN 4279) 



WIND-TUNNEL INVESTIGATION OF THE HIGH- 
SUBSONIC STATIC LONGITUDINAL STABILITY 
CHARACTERISTICS OF SEVERAL WING-BODY CON- 
FIGURATIONS DESIGNED FOR HIGH LIFT -DRAG 
RATIOS AT A MACH NUMBER OF 1.4. Paul G. 
Fournier. July 1958. 42p. diagrs., photo., tab. 
(NACA TN 4340) 



144 



(1) AERODYNAMICS 



LOW-SPEED EXPERIMENTAL DETERMINATION OF 
THE EFFECTS OF LEADING-EDGE RADIUS AND 
PROFILE THICKNESS ON STATIC AND OSCILLA- 
TORY LATERAL STABILITY DERIVATIVES FOR A 
DELTA WING WITH 60° OF LEADING-EDGE SWEEP. 
Hermans. Fletcher. July 1958- 45p. diagrs., 
photos., tabs. (NACA TN 4341) 



EXPLORATORY WIND-TUNNEL INVESTIGATION 
AT HIGH SUBSONIC AND TRANSONIC SPEEDS OF 
JET FLAPS ON UNSWEPT RECTANGULAR WINGS. 
Vernard E. Lockwood and Raymond D. Vogler. 
August 1958. 37p. diagrs. (NACA TN 4353) 



THE EFFECTS OF AN INVERSE-TAPER LEADING- 
EDGE FLAP ON THE AERODYNAMIC CHARACTER- 
ISTICS IN PITCH OF A WING-BODY COMBINATION 
HAVING AN ASPECT RATIO OF 3 AND 45° OF 
SWEEPBACK AT MACH NUMBERS TO 0.92. Fred A. 
Demele and K. Harmon Powell. August 1958. 57p. 
diagrs., photo., tabs. (NACA TN 4366) 



USE OF THE COANDA EFFECT FOR JET DEFLEC- 
TION AND VERTICAL LIFT WITH MULTIPLE -FLAT - 
PLATE AND CURVED-PLATE DEFLECTION SUR- 
FACES. UweH. vonGlahn. APPENDIX B: 
ESTIMATED PERFORMANCE OF MULTIPLE- FLAT - 
PLATE DEFLECTORS. Thomas F. Gelder. 
September 1958. 54p. diagrs., photo., tabs. 
(NACA TN 4377) 



COMPARISON OF SHOCK -EXPANSION THEORY 
WITH EXPERIMENT FOR THE LIFT, DRAG, AND 
PITCHING-MOMENT CHARACTERISTICS OF TWO 
WING-BODY COMBINATIONS AT M = 5.0. 
Raymond C. Savin. September 1958. 13p. diagrs. 
(NACA TN 4385) 



STATIC LONGITUDINAL AND LATERAL STABILITY 
CHARACTERISTICS AT LOW SPEED OF 60° 
SWEPTBACK-MIDWING MODELS HAVING WINGS 
WITH AN ASPECT RATIO OF 2, 4, OR 6. Walter D. 
Wolhart and David F. Thomas, Jr. September 1958. 
41p. diagrs., tabs. (NACA TN 4397) 



(1.8.1.1.2) 

Lateral 



LATERAL STABILITY AND CONTROL CHARACTER- 
ISTICS OF AN AIRPLANE MODEL HAVING A 42.8° 
SWEPTBACK CIRCULAR-ARC WING WITH ASPECT 
RATIO 4.00, TAPER RATIO 0.50, AND SWEPTBACK 
TAIL SURFACES. Kenneth W. Goodson and Paul 
Comisarow. October 17, 1947. 72p. diagrs., 
photos., tab. (NACA RM L7G31) 



INVESTIGATION OF THE DYNAMIC LATERAL 
STABnJTY AND CONTROL CHARACTERISTICS OF 
A MODEL OF A FIGHTER AIRPLANE WITHOUT A 
HORIZONTAL TAIL AND EQUIPPED WITH EITHER 
SINGLE OR TWIN VERTICAL TAILS. John W. ■ 
Draper and Robert W. Rose. November 15, 1949. 
20p. diagrs., photos., tab. (NACA RM L9J07a) 



WIND-TUNNEL TESTS OF A 0.16-SCALE MODEL 
OF THE X-3 AIRPLANE AT HIGH SUBSONIC 
SPEEDS. STABILITY AND CONTROL CHARACTER- 
ISTICS. William T. Hamilton and Joseph W. Cleary. 
April 21, 1950. 129p. diagrs., photos., tabs. 
(NACA RM A50A03) 



WIND-TUNNEL TESTS OF A 0.16-SCALE MODEL 
OF THE X-3 AIRPLANE AT HIGH SUBSONIC SPEEDS. 
- ADDITIONAL STABILITY AND CONTROL CHAR- 
ACTERISTICS AND THE AERODYNAMIC EFFECTS 
OF EXTERNAL STORES AND RAM JETS . Joseph W. 
Cleary and Jack A. Me lie nthin. June 13, 1950. 86p. 
diagrs., photos., tabs. (NACA RM A50C30) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR-ARC SECTIONS AND 40<> SWEEPBACK. 
STATIC LATERAL STABILITY CHARACTERISTICS 
AT MACH NUMBERS OF 1.40 AND 1.59. M. Leroy 
Spearman. June 14, 1950. 28p. diagrs., photos., 
tab. (NACA RM L50C17) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR-ARC SECTIONS AND 40<> SWEEPBACK. 
STATIC LATERAL CONTROL CHARACTERISTICS 
AT MACH NUMBERS OF 1.40 AND 1.59. Ross B. 
Robinson. November 10, 1950. 40p. diagrs., 
photos., tabs. (NACA RM L50I11) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR -ARC SECTIONS AND 40° SWEEPBACK. 
FORCE CHARACTERISTICS OF THE COMPLETE 
CONFIGURATION AND ITS VARIOUS COMPONENTS 
AT MACH NUMBERS OF 1.40 AND 1.59. Norman F. 
Smith and Jack E . Marte. January 22, 1951. 55p. 
diagrs., photos., tab. (NACA RM L50K14) 



AERODYNAMIC CHARACTERISTICS AT SUPER- 
SONIC SPEEDS OF A SERIES OF WING-BODY 
COMBINATIONS HAVING CAMBERED WINGS WITH 
AN ASPECT RATIO OF 3.5 AND A TAPER RATIO OF 
0.2. EFFECTS OF SWEEP ANGLE AND THICKNESS 
RATIO ON THE STATIC LATERAL STABILITY 
CHARACTERISTICS AT M = 1.60. M. Leroy 
Spearman and John H. Hilton, Jr. January 1952. 
31p. diagrs., tabs. (NACA RM L51K15a) 



THE AERODYNAMIC CHARACTERISTICS OF A 
SUPERSONIC AIRCRAFT CONFIGURATION WITH A 
40° SWEPTBACK WING THROUGH A MACH NUM- 
BER RANGE FROM TO 2.4 AS OBTAINED FROM 
VARIOUS SOURCES. M. Leroy Spearman and Ross 
B. Robinson. April 1952. 50p. diagrs., photo., 
tab. (NACA RM L52A21) 



EXPERIMENTAL INVESTIGATION OF THE STATIC 
AERODYNAMIC AND DYNAMIC DAMPING-IN-ROLL 
CHARACTERISTICS OF AN 8-CM AIRCRAFT 
ROCKET WITH SOLID AND SLOTTED FINS. Robert 
S. Chubb. June 1952. ii, 43p. diagrs., photo. 
(NACA RM A52C04) 



AERODYNAMIC CHARACTERISTICS AT SUPER- 
SONIC SPEEDS OF A SERIES OF WING-BODY COM- 
BINATIONS HAVING CAMBERED WINGS WITH AN 
ASPECT RATIO OF 3.5 AND A TAPER RATIO OF 
0.2. EFFECTS OF SWEEP ANGLE AND THICKNESS 
RATIO ON THE STATIC LATERAL STABILITY 
CHARACTERISTICS AT M = 2.01. Clyde V. 
Hamilton. August 1952. 37p. diagrs., tabs. 
(NACA RM L52E23) 



LOW-SPEED STATIC LONGITUDINAL AND LAT- 
ERAL STABILITY CHARACTERISTICS OF A MODEL 
WITH LEADING-EDGE CHORD-EXTENSIONS INCOR- 
PORATED ON A 40° SWEPTBACK CIRCULAR-ARC 
WING OF ASPECT RATIO 4 AND TAPER RATIO 0.50. 
Kenneth W. Goodson and Albert G. Few, Jr 
November 1952. 46p. diagrs., photos., tab. 
(NACA RM L52I18) 



( 1 ) AERODYNAMICS 



145 



WIND-TUNNEL INVESTIGATION OF A RAM-JET 
MISSILE MODEL HAVING A WING AND CANARD 
SURFACES OF DELTA PLAN FORM WITH 70° 
SWEPT LEADING EDGES. FORCE AND MOMENT 
CHARACTERISTICS OF VARIOUS COMBINATIONS 
OF COMPONENTS AT A MACH NUMBER OF 1 .6. 
Clyde V. Hamilton, Cornelius Driver, and John R. 
Sevier, Jr. March 1953. 48p. diagrs., photo., 
tabs. (NACA RM L53AI4) 



INVESTIGATION OF SPOILER AILERONS WITH AND 
WITHOUT A GAP BEHIND THE SPOILER ON A 45° 
SWEPTBACK WING-FUSELAGE COMBINATION AT 
MACH NUMBERS FROM 0.60 TO 1.03. F. E. West, 
Jr., William Solomon, and Edward M. Brummal. 
September 1953. 38p. diagrs. (NACA RM L53G07a) 



THEORETICAL CALCULATIONS OF THE STABILI- 
TY DERIVATIVES AT SUPERSONIC SPEEDS FOR A 
HIGH-SPEED AIRPLANE CONFIGURATION. 
Kenneth Margolis and Percy J. Bobbitt. October 
1953. 59p. diagrs., tab. (NACA RM L53G17) 



LOW-SPEED STATIC STABILITY AND CONTROL 
CHARACTERISTICS OF A 1/4-SCALE MODEL OF 
THE BELL X-l AIRPLANE EQUIPPED WITH A 
4-PERCENT -THICK, ASPECT-RATIO-4, UNSWEPT 
WING. WiUiamC. Moseley, Jr., and Robert T. 
Taylor. November 1953. 53p. diagrs., photos., 
tab. (NACARM L53H27) 



STATIC LATERAL STABILITY CHARACTERISTICS 
OF A 1/16-SCALE MODEL OF THE DOUGLAS 
D- 558-11 RESEARCH AIRPLANE AT MACH NUM- 
BERS OF 1.61 AND 2.01. Frederick C. Grant and 
Ross B. Robinson. November 1953. 39p. diagrs., 
photo., tabs. (NACA RM L53I29a) 



EFFECT OF LARGE DEFLECTIONS OF A CANARD 
CONTROL AND DEFLECTIONS OF A WING-TIP 
CONTROL ON THE STATIC -STABILITY AND 
INDUCED-ROLL CHARACTERISTICS OF A CRUCI- 
FORM CANARD MISSILE AT A MACH NUMBER OF 
2.01. M. Leroy Spearman. December 1953. 20p. 
diagrs., tabs. (NACA RM L53K03) 



AERODYNAMIC CHARACTERISTICS OF A 
CRUCIFORM -WING MISSILE WITH CANARD CON- 
TROL SURFACES AND OF SOME VERY SMALL 
SPAN WING-BODY MISSILES AT A MACH NUMBER 
OF 1.41. M. Leroy Spearman and Ross B. 
Robinson. April 1954. 27p. diagrs., tabs. 
(NACA RM L54B11) 



EFFECTS OF CANOPY, REVISED VERTICAL TAIL, 
AND A YAW-DAMPER VANE ON THE AERODYNAM- 
IC CHARACTERISTICS OF A 1/16-SCALE MODEL 
OF THE DOUGLAS D-558-H RESEARCH AIRPLANE 
AT A MACH NUMBER OF 2.01. Ross B. Robinson. 
August 1954. 29p. diagrs., tabs. 
(NACA RM L54F25) 



STABILITY AND DRAG CHARACTERISTICS AT 
MACH NUMBERS FROM 0.8 TO 1.5 OF A FREE- 
FLIGHT MODEL HAVING 3-PERCENT-THICK, 60° 
TRIANGULAR WING AND HORIZONTAL TAIL SUR- 
FACES. Rowe Chapman, Jr., and Harvey A. 
Wallskog. August 1954. 30p. diagrs., photos., tab. 
(NACA RM L54G23a) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR-ARC SECTIONS AND 40° SWEEPBACK. 
STABILITY AND CONTROL CHARACTERISTICS AT 
A MACH NUMBER OF 1.61 OF THE COMPLETE 
CONFIGURATION EQUIPPED WITH SPOILERS. 
Clyde V. Hamilton and Cornelius Driver. September 
1954. 28p. diagrs. (NACA RM L54F15) 



LOW-SPEED MEASUREMENT OF STATIC STABIL- 
ITY AND DAMPING DERIVATIVES OF A 60° 
DELTA-WING MODEL FOR ANGLES OF ATTACK 
OF 0° TO 90°. Donald E. Hewes. September 1954. 
30p. diagrs., photo., tab. (NACA RM L54G22a) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR-ARC SECTIONS AND 40° SWEEPBACK. 
STATIC LONGITUDINAL AND LATERAL STABILITY 
AND CONTROL CHARACTERISTICS AT A MACH 
NUMBER OF 1.89. M. Leroy Spearman and Edward 
B. Palazzo. October 1954. 24p. diagrs., photo., 
tab. (NACA RM L54G26a) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR-ARC SECTIONS AND 40° SWEEPBACK. 
AERODYNAMIC CHARACTERISTICS OF THE CON- 
FIGURATION EQUIPPED WITH A CANARD CON- 
TROL SURFACE AT A MACH NUMBER OF 1.89. 
M. Leroy Spearman and Edward B. Palazzo. 
October 1954. 22p. diagrs., photo., tab. 
(NACA RM L54H19) 



LATERAL MOTIONS ENCOUNTERED WITH THE 
DOUGLAS D-558-II ALL-ROCKET RESEARCH AIR- 
PLANE DURING EXPLORATORY FLIGHTS TO A 
MACH NUMBER OF 2.0. Herman O. Ankenbruck 
and Chester H. Wolowicz. December 1954. 32p. 
diagrs., photos., tab. (NACA RM H54I27) 



LOW -SPEED MEASUREMENTS OF ROLLING AND 
YAWING STABILITY DERIVATIVES OF A 60° 
DELTA-WING MODEL. Joseph L. Johnson, Jr. 
December 1954. 17p. diagrs., tab. 
(NACA RM L54G27) 



PRELIMINARY LOW-SPEED WIND-TUNNEL INVES- 
TIGATION OF SOME ASPECTS OF THE AERODY- 
NAMIC PROBLEMS ASSOCIATED WITH MISSILES 
CARRIED EXTERNALLY IN POSITIONS NEAR AIR- 
PLANE WINGS. William J. Alford, Jr., H. Norman 
Silvers, and Thomas J. King, Jr. December 1954. 
30p. diagrs., photos., tab. (NACARM L54J20) 



FLIGHT EXPERIENCE WITH TWO HIGH-SPEED 
AIRPLANES HAVING VIOLENT LATERAL- 
LONGITUDINAL COUPLING IN AILERON ROLLS. 
NACA High-Speed Flight Station. February 1955. 
30p. diagrs., photos., tabs. (NACA RM H55A13) 



INVESTIGATION OF THE LATERAL STABILITY 
CHARACTERISTICS OF THE DOUGLAS X-3 CON- 
FIGURATION AT MACH NUMBERS FROM 0.6 TO 
1.1 BY MEANS OF A ROCKET -PROPELLED 
MODEL. Jesse L. Mitchell and Robert F. Peck. 
February 1955. 37p. diagrs., photo., tabs. 
(NACA RM L54L20) 



146 



(1) AERODYNAMICS 



THE ROLLING MOMENT DUE TO SIDESLIP OF 
SWEPT WINGS AT SUBSONIC AND TRANSONIC 

SPEEDS . Edward C . Polhamus and William C . 
Sleeman, Jr. March 1955* 81p. diagrs., photos., 
tabs. (NACARM L54L01) 



EXPLORATORY INVESTIGATION OF THE LOW- 
SPEED STATIC STABILITY OF A CONFIGURATION 
EMPLOYING THREE IDENTICAL TRIANGULAR 
WING PANELS AND A BODY OF EQUAL LENGTH. 
NoelK. Delany., April 1955. 25p. diagrs., photos. 
(NACA RM A55C28) 



LATERAL STABILITY CHARACTERISTICS AT LOW 
LIFT BETWEEN MACH NUMBERS OF 0.85 AND 1.15 
OF A ROCKET-PROPELLED MODEL OF A SUPER- 
SONIC AIRPLANE CONFIGURATION HAVING A 
TAPERED WING WITH CIRCULAR-ARC SECTIONS 
AND 40° SWEEPBACK. Charles T. D'Aiutolo and 
Allen B. Henning. April 1955. 50p. diagrs., 
photos ., tabs. (NACA RM L55A31) 



COMPARISON OF THE STATIC STABILITY OF A 
68.7° DELTA-WING MODEL WITH DIHEDRAL AND 
A TWISTED AND CAMBERED WING MODEL OF THE 
SAME PLAN FORM. John W. Paulson. April 1955. 
18p. diagrs., tab. (NACA RM L55B11) 



LATERAL STABILITY AND CONTROL CHARACTER- 
ISTICS OF THE CONVAIR XF-92A DELTA-WING 
AIRPLANE AS MEASURED IN FLIGHT. Thomas R. 
Sisk and Duane O. Muhleman. May 1955. 55p. 
diagrs., photos., tabs. (NACA RM H55A17) 



ADDITIONAL MEASUREMENTS OF THE LOW- 
SPEED STATIC STABILITY OF A CONFIGURATION 
EMPLOYING THREE TRIANGULAR WING PANELS 
AND A BODY OF EQUAL LENGTH. Noel K. Delany. 
July 1955. 31p. diagrs. (NACARM A55F02a) 



STABILITY AND CONTROL CHARACTERISTICS 
OBTAINED DURING DEMONSTRATION OF THE 
DOUGLAS X-3 RESEARCH AIRPLANE. Richard E. 
Day and Jack Fischel. July 1955. 51p. diagrs., 
photos., tab. (NACA RM H55E16) 



EFFECT OF SEVERAL WING MODIFICATIONS ON 
THE LOW-SPEED STALLING CHARACTERISTICS OF 
THE DOUGLAS D-558-H RESEARCH AIRPLANE. 
Jack Fischel and Donald Reisert. July 1955. 62p. 
diagrs., photos., tabs. (NACA RM H55E31a) 



FLIGHT MEASUREMENTS OF THE LATERAL 
RESPONSE CHARACTERISTICS OF THE CONVAIR 
XF-92A DELTA-WING AIRPLANE. Euclid C. 
Holleman. August 1955, 37p. diagrs., tabs. 
(NACA RM H55E26) 



WIND-TUNNEL MEASUREMENTS OF THE DYNAMIC 
CROSS DERIVATIVE C; - C ( . (ROLLING MO- 
MENT DUE TO YAWING VELOCITY AND TO AC- 
CELERATION IN SIDESLIP) OF THE DOUGLAS 
D-558-II AIRPLANE AND ITS COMPONENTS AT 
SUPERSONIC SPEEDS INCLUDING DESCRIPTION 
OF THE TECHNIQUE. William B. Boatright. 
November 1955. 57p. diagrs., photos. 
(NACA RM L55H16) 



WIND-TUNNEL INVESTIGATION AT TRANSONIC 
SPEEDS OF A JET CONTROL ON AN 80° DELTA- 
WING MISSILE. Thomas R. Turner and Raymond D. 
Vogler. November 1955. 32p, diagrs. 
(NACA RM L55H22) 



EFFECT OF LARGE NEGATD/E DIHEDRAL OF THE 
HORIZONTAL TAIL ON LONGITUDINAL AND LAT- 
ERAL STABILITY CHARACTERISTICS OF A 
SWEPT- WIN G CONFIGURATION AT TRANSONIC 
SPEEDS. Donald D. Arabian. January 1956. 24p. 
diagrs., photos. (NACA RM L55I20) 



WIND-TUNNEL INVESTIGATION AT HIGH SUBSONIC 
SPEEDS OF SOME EFFECTS OF FUSELAGE CROSS- 
SECTION SHAPE AND WING HEIGHT ON THE STAT- 
IC LONGITUDINAL AND LATERAL STABILITY 
CHARACTERISTICS OF A MODEL HAVING A 45° 
SWEPT WING- Thomas J. King, Jr. February 
1956. 6 lp. diagrs., photo. (NACA RM L55J25) 



SOME EFFECTS OF AILERONS ON THE VARIATION 
OF AERODYNAMIC CHARACTERISTICS WITH SIDE- 
SLIP AT LOW SPEED. Kenneth W. Goodson. 
March 1956. 40p. diagrs., tab. (NACA RM L55L20) 



LOW-SPEED STATIC STABILITY CHARACTERIS- 
TICS OF A CAMBERED-DELTA-WING MODEL. 
John M. Riebe and William C. Moseley, Jr. March 
1956. 27p. diagrs. (NACA RM L55L21a) 



LOW-SPEED INVESTIGATION OF THE EFFECTS 
OF WING DIHEDRAL ANGLE AND FIN LENGTH ON 
THE STATIC STABILITY CHARACTERISTICS OF A 
MODEL HAVING AN 82° DELTA WING. Kenneth P. 
Spreemann. April 1956. 30p. diagrs. 
(NACA RM L55L30a) 



AN EXPERIMENTAL STUDY AT HIGH SUBSONIC 
SPEEDS OF SEVERAL TAIL CONFIGURATIONS ON 
A MODEL WITH AN UNSWEPT WING. William C. 
Sleeman, Jr. April 1956. 67p. diagrs., photos. 
(NACA RM L56A06a) 



LATERAL STABILITY CHARACTERISTICS BE- 
TWEEN MACH NUMBERS OF 0.80 AND 1.57 AND 
SIMULATION OF COUPLED MOTION AT MACH 
NUMBER 1.30 OF A ROCKET -PROPELLED MODEL 
OF AN AIRPLANE CONFIGURATION HAVTN.G THIN 
HIGHLY TAPERED 45° SWEPTBACK SURFACES. 
Charles T. D'Aiutolo and Allen B. Henning. April 
1956. 41p. diagrs., photos., tabs. 
(NACA RM L56A17) 



A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
STORE AND HORIZONTAL-TAIL LOADS AND SOME 
EFFECTS OF FUSELAGE -AFTERBODY MODIFICA- 
TIONS ON A SWEPT -WING FIGHTER AIRPLANE. 
Joseph M. Hallissy, Jr., and Louis Kudlacik . April 
1956. 79p. diagrs., photos. (NACA RM L56A26) 



LOW -SPEED MEASUREMENTS OF STATIC STABIL- 
ITY, DAMPING IN YAW, AND DAMPING IN ROLL 
OF A DELTA, A SWEPT, AND AN UNSWEPT WING 
FOR ANGLES OF ATTACK FROM 0<> TO 90°. 
Joseph L. Johnson, Jr. April 1956. 19p. diagrs., 
tabs. (NACA RM L56B01) 



INVESTIGATION AT HIGH SUBSONIC SPEEDS OF 
THE EFFECT OF HORIZONTAL-TAIL LOCATION 
ON LONGITUDINAL AND LATERAL STABILITY 
CHARACTERISTICS OF A COMPLETE MODEL 
HAVING A SWEPTBACK WING IN A HIGH LOCA- 
TION. H. Norman Silvers and Thomas J. King, Jr. 
April 1956. 46p. diagrs., tab. (NACA RM L56B10) 



147 



(1) AERODYNAMICS 



WIND-TUNNEL INVESTIGATION OF A RAM-JET 
MISSILE MODEL HAVING A WING AND CANARD 
SURFACES OF DELTA PLAN FORM WITH 70° 
SWEPT LEADING EDGES FORCE AND MOMENT 
CHARACTERISTICS AT COMBINED ANGLES OF 
PITCH AND SIDESLIP FOR MACH NUMBER 2.01. 
Cornelius Driver and Clyde V. Hamilton. April 
1956. 67p, diagrs., photo., tabs- 
(NACA RM L56B21) 



THE EFFECT.OF CONICAL CAMBER ON THE 
STATIC LONGITUDINAL, LATERAL, AND DIREC- 
TIONAL CHARACTERISTICS OF A 45° SWEPTBACK 
WING AT MACH NUMBERS UP TO 0.96. Robert I. 
Sammonds and Robert M. Reynolds. July 1956. 
64p. diagrs., tabs. (NACA RM A56D02) 



LOW-SPEED WIND-TUNNEL RESULTS FOR A THDJ 
ASPECT -RATIO-1. 85 POINTED-WING-FUSELAGE 
MODEL WITH DOUBLE SLOTTED FLAPS. Albert 
E. Brown. July 1956. 31p. diagrs., tabs. 
(NACA RM L56D03) 



SOME EFFECTS OF WING FENCES ON THE LATER- 
AL STABILITY DERIVATIVES OF A 60° DELTA 
WING OSCILLATING CONTINUOUSLY IN YAW. 
Donald R. Riley. July 1956. 29p. diagrs., photos., 
tab. (NACA RM L56D13) 



WIND-TUNNEL INVESTIGATION AT HIGH SUBSONIC 
SPEEDS OF JET, SPOILER, AND AILERON CON- 
TROLS ON A 1/16-SCALE MODEL OF THE DOUGLAS 
D-558-H RESEARCH AIRPLANE. Raymond D. 
Vogler. July 1956. 52p. diagrs., photo., tabs. 
(NACA RM L56E25) 



WIND-TUNNEL INVESTIGATION OF THE EFFECTS 
OF WING THICKNESS ON THE STATIC LONGITU- 
DINAL AND LATERAL STABILITY OF UNSWEPT 
WINGS OF ASPECT RATIO 3 AT HIGH SUBSONIC 
SPEEDS. William C. Hayes, Jr., and Edward C. 
Polhamus. August 1956. 43p. diagrs., photos. 
(NACA RM L56E30a) 



EFFECT OF WING HEIGHT AND DIHEDRAL ON THE 
LATERAL STABILITY CHARACTERISTICS AT LOW 
LIFT OF A 45° SWEPT -WING AIRPLANE CONFIG- 
URATION AS OBTAINED FROM TIME -VECTOR 
ANALYSES OF ROCKET -PROPELLED-MODEL 
FLIGHTS AT MACH NUMBERS FROM 0.7 TO 1.3. 
Clarence L. Gillis and Rowe Chapman, Jr. 
September 1956. 70p. diagrs., photos., tabs. 
(NACA RM L56E17) 



INVESTIGATION OF SPOILER-SLOT-DEFLECTOR 
AILERONS AND OTHER SPOILER AILERONS ON A 
45° SWEPTBACK-WING-FUSELAGE COMBINATION 
AT MACH NUMBERS FROM 0.60 TO 1.03. F. E. 
West, Jr., Charles F. Whitcomb, and James W. 
Schmeer. September 1956. 59p. diagrs., tab. 
(NACA RM L56F15) 



STATIC STABILITY CHARACTERISTICS OF A 
CAMBERED-DELTA-WING MODEL AT HIGH 
SUBSONIC SPEEDS. William C. Moseley, Jr. 
October 1956. 35p. diagrs., photos. 
(NACA RM L56H13) 



A LOW -SPEED INVESTIGATION OF A HIGH-LIFT 
LATERAL-CONTROL DEVICE CONSISTING OF A 
SPOILER-SLOT -DEFLECTOR AND A TRAILING- 
EDGE FLAP ON A TAPERED 45° SWEPTBACK 
WING. Alexander D. Hammond and Jarrett K. 
Huffman. October 1956. 21 p. diagrs. 
(NACA RM L56H31) 



FORCE TEST RESULTS FOR BODY-MOUNTED 
LATERAL CONTROLS AND SPEED BRAKES ON A 
45° SWEPT-WING MODEL AT MACH NUMBERS 
FROM 0.80 TO 0.98. F. E. West, Jr., and Chris C. 
Critzos. December 1956. 32p. diagrs., photos., 
tab. (NACA RM L56I05) 



EXPERIMENTAL AND PREDICTED LONGITUDINAL 
AND LATERAL-DIRECTIONAL RESPONSE CHAR- 
ACTERISTICS OF A LARGE FLEXIBLE 35° SWEPT- 
WING AIRPLANE AT AN ALTITUDE OF 35,000 FEET. 
Henry A. Cole, Jr., Stuart C Brown, and Euclid C, 
Holleman. 1957. ii, 39p. diagrs., photo., tabs. 
(NACA Rept. 1330. Supersedes RM A54H09; 
TN 3874) 



EXPERIMENTAL DETERMINATION AT SUBSONIC 
SPEEDS OF THE OSCILLATORY AND STATIC 
LATERAL STABILITY DERIVATIVES OF A SERIES 
OF DELTA WINGS WITH LEADING-EDGE SWEEP 
FROM 30<> TO 86.5°. William Letko. April 1957. 
38p. diagrs., photos., tab. (NACA RM L57A30) 



THE SUBSONIC STATIC AERODYNAMIC CHARAC- 
TERISTICS OF AN AIRPLANE MODEL HAVING A 
TRIANGULAR WING OF ASPECT RATIO 3. 
n - LATERAL AND DIRECTIONAL CHARACTERIS- 
TICS. Howard F. Savage and Bruce E. Tinling. 
August 1957. 82p. diagrs., photo., tabs. 
(NACA TN 4042. Supersedes RM A55B11) 



STATIC LONGITUDINAL AND LATERAL STABILITY 
CHARACTERISTICS AT LOW SPEED OF 45° 
SWEPTBACK-MIDWING MODELS HAVING WINGS 
WITH AN ASPECT RATIO OF 2, 4, OR 6. David F. 
Thomas, Jr., and Walter D. Wolhart. September 
1957. 30p. diagrs., photos., tabs. (NACA TN 4077) 



WIND-TUNNEL INVESTIGATION OF THE STATIC 
LATERAL STABILITY CHARACTERISTICS OF 
WING-FUSELAGE COMBINATIONS AT HIGH SUB- 
SONIC SPEEDS. TAPER-RATIO SERIES. James 
W. Wiggins and Paul G. Fournier. October 1957. 
25p. diagrs., photos. (NACA TN 4174, Supersedes 
RM L53B25a) 



EXPERIMENTAL INVESTIGATION OF THE 
LATERAL TRIM OF A WING-PROPELLER COM- 
BINATION AT ANGLES OF ATTACK UP TO 90° 
WITH ALL PROPELLERS TURNING IN THE SAME 
DIRECTION. William A. Newsom, Jr. January 
1958. 27p. diagrs. (NACA TN 4190) 



SUBSONIC FLIGHT INVESTIGATION OF METHODS 
TO IMPROVE THE DAMPING OF LATERAL OSCIL- 
LATIONS BY MEANS OF A VISCOUS DAMPER IN 
THE RUDDER SYSTEM IN CONJUNCTION WITH 
ADJUSTED HINGE-MOMENT PARAMETERS. 
Harold L. Crane, George J. Hurt, Jr., and 
John M. Elliott. January 1958. 45p. diagrs., 
photos,, tab. (NACA TN 4193. Supersedes 
RM L54D09) 



148 



(1) AERODYNAMICS 



LOW-SUBSONIC INVESTIGATION TO DETERMINE 
THE CHORDWISE PRESSURE DISTRIBUTION AND 
EFFECTIVENESS OF SPOILERS ON A THIN, LOW- 
ASPECT-RATIO, UNSWEPT, UNTAPERED, SEMI- 
SPAN WING AND ON THE WING WITH LEADING- 
AND TRAILING-EDGE FLAPS. Delwin R. Croom. 
April 1958. 133p. diagrs., tabs. 
(NACA RM L58B05) 



AERODYNAMIC RESEARCH ON FUSELAGES WITH 
RECTANGULAR CROSS SECTION. (Aerodynamische 
Untersuchungen an Rumpfen mit rechteckahnlichem 
Querschnitt.) K. Maruhn. July 1958. 37p. diagrs. 
(NACA TM 1414. Translation from Jahrbiich 1942 
der deutschen Luftfahrtforschung, p. 263-279.) 



WIND-TUNNEL INVESTIGATION OF EFFECTS OF 
SPOILER LOCATION, SPOILER SIZE, AND FUSE- 
LAGE NOSE SHAPE ON DIRECTIONAL CHARACTER- 
ISTICS OF A MODEL OF A TANDEM-ROTOR HELI- 
COPTER FUSELAGE. James L. Williams. July 
1958. 44p. diagrs., photos., tab. (NACA TN 4305) 



LOW-SPEED EXPERIMENTAL DETERMINATION OF 
THE EFFECTS OF LEADING-EDGE RADIUS AND 
PROFILE THICKNESS ON STATIC AND OSCILLA- 
TORY LATERAL STABILITY DERIVATIVES FOR A 
DELTA WING WITH 6(P OF LEADING-EDGE SWEEP. 
Hermans. Fletcher. July 1958. 45p. diagrs., 
photos., tabs. (NACA TN 4341) 



STATIC LONGITUDINAL AND LATERAL STABILITY 
CHARACTERISTICS AT LOW SPEED OF 60° 
SWEPTBACK-MIDWING MODELS HAVING WINGS 
WITH AN ASPECT RATIO OF 2, 4, OR 6. Walter D. 
Wolhart and David F. Thomas, Jr. September 1958. 
41p. diagrs., tabs. (NACA TN 4397) 



(1.8.1. 1-3) 
Directional 



LATERAL STABILITY AND CONTROL CHARACTER- 
ISTICS OF AN AIRPLANE MODEL HAVING A 42.8° 
SWEPTBACK CIRCULAR-ARC WING WITH ASPECT 
RATIO 4.00, TAPER RATIO 0.50, AND SWEPTBACK 
TAIL SURFACES. Kenneth W. Goodson and Paul 
Comisarow. October 17, 1947. 72p. diagrs., 
photos., tab. (NACA RM L7G31) 



SUPERSONIC -TUNNEL TESTS OF TWO SUPER- 
SONIC AIRPLANE MODEL CONFIGURATIONS. 
Macon C. Ellis, Jr., Lowell E. Hasel, and Carl E. 
Grigsby. December 31, 1947. 49p. diagrs., 
photos., tab. (NACA RM L7J15) 



FLIGHT TESTS AT TRANSONIC AND SUPERSONIC 
SPEEDS OF AN AIRPLANE -LIKE CONFIGURATION 
WITH THIN STRAIGHT SHARP-EDGE WINGS AND 
TAIL SURFACES. Clarence L. Gillis and Jesse L. 
Mitchell. January 5, 1949. 37p. diagrs., photos., 
tab. (NACA RM L8K04a) 



INVESTIGATION OF THE DYNAMIC LATERAL 
STABILITY AND CONTROL CHARACTERISTICS OF 
A MODEL OF A FIGHTER AIRPLANE WITHOUT A 
HORIZONTAL TAIL AND EQUIPPED WITH EITHER 
SINGLE OR TWIN VERTICAL TAILS. John W. 
Draper and Robert W. Rose. November 15, 1949. 
20p. diagrs., photos., tab. (NACA RM L9J07a) 



WIND-TUNNEL TESTS OF A 0.16-SCALE MODEL 
OF THE X-3 AIRPLANE AT HIGH SUBSONIC 
SPEEDS. STABILITY AND CONTROL CHARACTER- 
ISTICS. William T. Hamilton and Joseph W. Cleary. 
April 21, 1950. 129p. diagrs., photos., tabs. 
(NACA RM A50A03) 



WIND-TUNNEL TESTS OF A 0.16-SCALE MODEL 
OF THE X-3 AIRPLANE AT HIGH SUBSONIC SPEEDS. 
- ADDITIONAL STABILITY AND CONTROL CHAR- 
ACTERISTICS AND THE AERODYNAMIC EFFECTS 
OF EXTERNAL STORES AND RAM JETS. Joseph W. 
Cleary and Jack A. Mellenthin. June 13, 1950. 86p. 
diagrs., photos., tabs. (NACA RM A50C30) 



PRELIMINARY RESULTS OF THE FLIGHT INVES- 
TIGATION BETWEEN MACH NUMBERS OF 0.80 AND 
1.36 OF A ROCKET -POWERED MODEL OF A 
SUPERSONIC AIRPLANE CONFIGURATION HAVING 
A TAPERED WING WITH CIRCULAR-ARC SECTIONS 
AND 40° SWEEPBACK. Charles T. D'Aiutolo and 
Homer P. Mason. October 31, 1950. 30p. diagrs., 
photos., tab. (NACA RM L50H29a) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR -ARC SECTIONS AND 40° SWEEPBACK. 
STATIC LATERAL CONTROL CHARACTERISTICS 
AT MACH NUMBERS OF 1.40 AND 1.59. Ross B. 
Robinson. November 10, 1950. 40p. diagrs., 
photos., tabs. (NACA RM L50I11) 



AN INVESTIGATION OF THE LONGITUDINAL 
CHARACTERISTICS OF THE X-3 CONFIGURATION 
USING ROCKET-PROPELLED MODELS. PRELIMI- 
NARY RESULTS AT MACH NUMBERS FROM 0.65 
TO 1.25. Jesse L. Mitchell and Robert F. Peck. 
December 1, 1950. 30p. diagrs. t photos. 
(NACA RM L50J03) 



AN INVESTIGATION OF THE LONGITUDINAL CHAR- 
ACTERISTICS OF THE X-3 CONFIGURATION WITH 
WING AND HORIZONTAL TAIL SURFACES OF 
ASPECT RATIO 3.0 BY MEANS OF ROCKET- 
PROPELLED MODELS. RESULTS AT HIGH LIFT 
COEFFICIENTS. Robert F. Peck and Jesse L. 
Mitchell. August 27, 1951. 3 4p. diagrs., photos. 
(NACARM L51G10) 



A WIND-TUNNEL INVESTIGATION OF THE STATIC 
STABILITY CHARACTERISTICS OF A l/8-SCALE 
EJECTABLE PILOT -SEAT COMBINATION AT A 
MACH NUMBER OF 0.8. Fioravante Visconti and 
Robert J. Nuber. December 1951. 29p. diagrs., 
photo s . (NACA RM L5 1H08) 



THE AERODYNAMIC CHARACTERISTICS OF A 
SUPERSONIC AIRCRAFT CONFIGURATION WITH A 
40° SWEPTBACK WING THROUGH A MACH NUM- 
BER RANGE FROM TO 2.4 AS OBTAINED FROM 
VARIOUS SOURCES. M. Leroy Spearman and Ross 
B. Robinson. April 1952. 50p. diagrs., photo., 
tab. (NACA RM L52A21) 



EXPERIMENTAL INVESTIGATION OF THE STATIC 
AERODYNAMIC AND DYNAMIC DAMPING-IN-ROLL 
CHARACTERISTICS OF AN 8-CM AIRCRAFT 
ROCKET WITH SOLID AND SLOTTED FINS. Robert 
S. Chubb. June 1952. ii, 43p. diagrs., photo. 
(NACA RM A52C04) 



149 



(1) AERODYNAMICS 



LOW -SPEED STATIC LONGITUDINAL AND LAT- 
ERAL STABILITY CHARACTERISTICS OF A MODEL 
WITH LEADING- EDGE CHORD- EXTENSIONS INCOR- 
PORATED ON A 40° SWEPTBACK CIRCULAR- ARC 
WING OF ASPECT RATIO 4 AND TAPER RATIO 0.50. 
Kenneth W. Goodson and Albert G. Few, Jr. 
November 1952. 46p. diagrs., photos., tab. 
(NACA RM L52I18) 



WIND-TUNNEL INVESTIGATION OF A RAM -JET 
MISSILE MODEL HAVING A WING AND CANARD 
SURFACES OF DELTA PLAN FORM WITH 70° 
SWEPT LEADING EDGES. FORCE AND MOMENT 
CHARACTERISTICS OF VARIOUS COMBINATIONS 
OF COMPONENTS AT A MACH NUMBER OF 1 -6. 
Clyde V. Hamilton, Cornelius Driver, and John R. 
Sevier, Jr. March 1953. 48p. diagrs., photo., 
tabs. (NACA RM L53A14) 



INVESTIGATION OF SPOILER AILERONS WITH AND 
WITHOUT A GAP BEHIND THE SPOILER ON A 45° 
SWEPTBACK WING-FUSELAGE COMBINATION AT 
MACH NUMBERS FROM 0.60 TO 1.03. F. E. West, 
Jr., William Solomon, and Edward M. Brummal. 
September 1953. 38p. diagrs. (NACA RM L53G07a) 



THEORETICAL CALCULATIONS OF THE STABILI- 
TY DERIVATIVES AT SUPERSONIC SPEEDS FOR A 
HIGH-SPEED AIRPLANE CONFIGURATION. 
Kenneth Margolis and Percy J. Bobbitt. October 
1953. 59p. diagrs., tab. (NACA RM L53G17) 



LOW-SPEED STATIC STABILITY AND CONTROL 
CHARACTERISTICS OF A 1/4-SCALE MODEL OF 
THE BELL X-l AIRPLANE EQUIPPED WITH A 
4-PERCENT-THICK, ASPECT-RATIO-4, UNSWEPT 
WING. William C. Moseley, Jr., and Robert T. 
Taylor. November 1953. 53p. diagrs., photos., 
tab. (NACA RM L53H2T) 



EFFECT OF LARGE DEFLECTIONS OF A CANARD 
CONTROL AND DEFLECTIONS OF A WING-TIP 
CONTROL ON THE STATIC -STABILITY AND 
INDUCED -ROLL CHARACTERISTICS OF A CRUCI- 
FORM CANARD MISSILE AT A MACH NUMBER OF 
2.01. M. Leroy Spearman. December 1953. 20p. 
diagrs., tabs. (NACA RM L53K03) 



AERODYNAMIC CHARACTERISTICS AT TRANSONIC 
AND SUPERSONIC SPEEDS OF A ROCKET- 
PROPELLED AIRPLANE CONFIGURATION HAVING 
A 52. 50 DELTA WING AND A LOW, SWEPT HORI- 
ZONTAL TAIL. Alan B. Kehlet. March 1954. 31p. 
diagrs., photos. (NACA RM L54A20) 



A FLIGHT INVESTIGATION AT TRANSONIC SPEEDS 
OF THE AERODYNAMIC CHARACTERISTICS OF A 
MODEL HAVING A THIN UNSWEPT WING OF 
ASPECT RATIO 3.1. Maurice D. White. August 
1954. 41p, diagrs., photo., tabs. 
(NACA RM A54F12) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR-ARC SECTIONS AND 40° SWEEPBACK. 
STABILITY AND CONTROL CHARACTERISTICS AT 
A MACH NUMBER OF 1.61 OF THE COMPLETE 
CONFIGURATION EQUIPPED WITH SPOILERS. 
Clyde V. Hamilton and Cornelius Driver. September 
1954. 28p. diagrs. (NACA RM L54F15) 



LOW-SPEED MEASUREMENT OF STATIC STABIL- 
ITY AND DAMPING DERIVATIVES OF A 60° 
DELTA- WING MODEL FOR ANGLES OF ATTACK 
OF 0O TO 90°. Donald E. Hewes. September 1954. 
30p. diagrs., photo., tab. (NACA RM L54G22a) 



AERODYNAMIC CHARACTERISTICS AT TRANSONIC 
AND SUPERSONIC SPEEDS OF A ROCKET- 
PROPELLED AIRPLANE CONFIGURATION HAVING 
A DIAMOND-PLAN-FORM WING OF ASPECT RATIO 
3.08 AND A LOW, SWEPT HORIZONTAL TAIL. 
Alan B. Kehlet. September 1954. 37p. diagrs., 
photos. (NACA RM L54G27a) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR -ARC SECTIONS AND 40° SWEEPBACK. 
STATIC LONGITUDINAL AND LATERAL STABILITY 
AND CONTROL CHARACTERISTICS AT A MACH 
NUMBER OF 1.89. M. Leroy Spearman and Edward 
B. Palazzo. October 1954. 24p. diagrs., photo., 
tab. (NACA RM L54G26a) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR-ARC SECTIONS AND 40<> SWEEPBACK. 
AERODYNAMIC CHARACTERISTICS OF THE CON- 
FIGURATION EQUD7PED WITH A CANARD CON- 
TROL SURFACE AT A MACH NUMBER OF 1.89. 
M. Leroy Spear man and Edward B. Palazzo. 
October 1954. 22p. diagrs., photo., tab. 
(NACARML54H19) 



LOW -SPEED MEASUREMENTS OF ROLLING AND 
YAWING STABILITY DERIVATIVES OF A 60° 
DELTA-WING MODEL. Joseph L. Johnson, Jr. 
December 1954. 17p. diagrs., tab. 
(NACA RM L54G27) 



EXPLORATORY INVESTIGATION OF THE LOW- 
SPEED STATIC STABILITY OF A CONFIGURATION 
EMPLOYING THREE IDENTICAL TRIANGULAR 
WING PANELS AND A BODY OF EQUAL LENGTH. 
Noel K. Delany. April 1955. 25p. diagrs., photos. 
(NACA RM A55C28) 



LATERAL STABILITY AND CONTROL CHARACTER- 
ISTICS OF THE CONVAIR XF-92A DELTA-WING 
AIRPLANE AS MEASURED IN FLIGHT. Thomas R. 
Sisk and Duane O. Muhleman. May 1955. 55p. 
diagrs., photos., tabs. (NACA RM H55A17) 



ADDITIONAL MEASUREMENTS OF THE LOW- 
SPEED STATIC STABILITY OF A CONFIGURATION 
EMPLOYING THREE TRIANGULAR WING PANELS 
AND A BODY OF EQUAL LENGTH. Noel K. Delany. 
July 1955. 31p. diagrs. (NACA RM A55F02a) 



STABILITY AND CONTROL CHARACTERISTICS 
OBTAINED DURING DEMONSTRATION OF THE 
DOUGLAS X-3 RESEARCH AIRPLANE. Richard E. 
Day and Jack Fischel. July 1955. 51p. diagrs., 
photos., tab. (NACA RM H55E16) 



A DISCUSSION OF RECENT WIND-TUNNEL STUDIES 
RELATING TO THE PROBLEM OF ESTIMATING 
VERTICAL- AND HORIZONTAL -TAIL LOADS. 
Richard E. Kuhn, Joseph M. Hallissy, Jr., and 
Ralph W. Stone, Jr. July 1955. 20p. diagrs., 
photos. (NACA RM L55El6a) 



150 



(1) AERODYNAMICS 



FLIGHT MEASUREMENTS OF THE LATERAL 
RESPONSE CHARACTERISTICS OF THE CONVAIR 
XF-92A DELTA-WING AIRPLANE. Euclid C. 
Holleman. August 1955. 37p. diagrs., tabs. 
(NACA RM H55E26) 



FLIGHT MEASUREMENTS OF DIRECTIONAL STA- 
BILITY TO A MACH NUMBER OF 1.48 FOR AN ■ 
AIRPLANE TESTED WITH THREE DIFFERENT 
VERTICAL TAIL CONFIGURATIONS. Hubert M. 
Drake, Thomas W. Finch, and James R. Peele. 
October 1955. 22p. diagrs., photos., tab. 
(NACA RM H55G26) 



EFFECT OF LAHGE NEGATIVE DIHEDRAL OF THE 
HORIZONTAL TAIL ON LONGITUDINAL AND LAT- 
ERAL STABILITY CHARACTERISTICS OF A 
SWEPT-WING CONFIGURATION AT TRANSONIC 
SPEEDS. Donald D. Arabian. January 1956. 24p. 
diagrs., photos. (NACA RM L55I20) 



SOME EFFECTS OF AILERONS ON THE VARIATION 
OF AERODYNAMIC CHARACTERISTICS WITH SIDE- 
SLIP AT LOW SPEED. Kenneth W. Goodson. 
March 1956. 40p. diagrs., tab. (NACA RM L55L20) 



LOW-SPEED STATIC STABILITY CHARACTERIS- 
TICS OF A CAMBERED -DELTA-WING MODEL. 
JohnM. Riebe and William C . Moseley, Jr. March 
1956. 27p. diagrs. (NACA RM L55L21a) 



LOW-SPEED INVESTIGATION OF THE EFFECTS 
OF WING DIHEDRAL ANGLE AND FIN LENGTH ON 
THE STATIC STABILITY CHARACTERISTICS OF A 
MODEL HAVING AN 82<> DELTA WING. Kenneth P. 
Spreemann. April 1956. 30p. diagrs. 
(NACARM L55L30a) 



AN EXPERIMENTAL STUDY AT HIGH SUBSONIC 
SPEEDS OF SEVERAL TAIL CONFIGURATIONS ON 
A MODEL WITH AN UNSWEPT WING. William C. 
S lee man, Jr. April 1956. 67p. diagrs., photos. 
(NACA RM L56A06a) 



A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
STORE AND HORIZONTAL-TAIL LOADS AND SOME 
EFFECTS OF FUSELAGE-AFTERBODY MODIFICA- 
TIONS ON A SWEPT-WING FIGHTER AIRPLANE. 
Joseph M. Hallissy, Jr., and Louis Kudlacik. April 
1956. 79p. diagrs., photos. (NACA RM L56A26) 



LOW -SPEED MEASUREMENTS OF STATIC STABIL- 
ITY, DAMPING IN YAW, AND DAMPING IN ROLL 
OF A DELTA, A SWEPT, AND AN UNSWEPT WING 
FOR ANGLES OF ATTACK FROM 0° TO 90<>. 
Joseph L. Johnson, Jr. April 1956. 19p. diagrs., 
tabs. (NACA RM L56B01) 



WIND-TUNNEL INVESTIGATION OF A RAM -JET 
MISSILE MODEL HAVING A WING AND CANARD 
SURFACES OF DELTA PLAN FORM WITH 70° 
SWEPT LEADING EDGES. FORCE AND MOMENT 
CHARACTERISTICS AT COMBttJED ANGLES OF 
PITCH AND STDESLEP FOR MACH NUMBER 2.01. 
Cornelius Driver and Clyde V. Hamilton. April 
1956. 67p. diagrs., photo., tabs. 
(NACA RM L56B21) 



EFFECT OF AIRPLANE CONFIGURATION ON 
STATIC STABILITY AT SUBSONIC AND TRANSONIC 
SPEEDS. Edward C. Polhamus and Joseph M. 
Hallissy, Jr. May 1956. 17p. diagrs. 
(NACA RM L56A09a) 



THE EFFECT OF CONICAL CAMBER ON THE 
STATIC LONGITUDINAL, LATERAL, AND DIREC- 
TIONAL CHARACTERISTICS OF A 45° SWEPTBACK 
WING AT MACH NUMBERS UP TO 0.96. Robert I. 
Sammonds and Robert M. Reynolds. July 1956. 
64p. diagrs., tabs. (NACA RM A56D02) 



LOW-SPEED WIND-TUNNEL RESULTS FOR A THIN 
ASPECT-RATIO-1.85 POINTED-WING-FUSELAGE 
MODEL WITH DOUBLE SLOTTED FLAPS. Albert 
E. Brown. July 1956. 31p. diagrs., tabs. 
(NACA RM L56D03) 



WIND-TUNNEL INVESTIGATION OF THE EFFECTS 
OF WING THICKNESS ON THE STATIC LONGITU- 
DINAL AND LATERAL STABILITY OF UNSWEPT 
WINGS OF ASPECT RATIO 3 AT HIGH SUBSONIC 
SPEEDS. William C. Hayes, Jr., and Edward C. 
Polhamus. August 1956. 43p. diagrs., photos. 
(NACA RM L56E30a) 



EFFECT OF WING HEIGHT AND DIHEDRAL ON THE 
LATERAL STABILITY CHARACTERISTICS AT LOW 
LIFT OF A 45° SWEPT-WING AIRPLANE CONFIG- 
URATION AS OBTAINED FROM TIME-VECTOR 
ANALYSES OF ROCKET -PROPELLED-MODEL 
FLIGHTS AT MACH NUMBERS FROM 0.7 TO 1.3. 
Clarence L. Gillis and Rowe Chapman, Jr. 
September 1956. 70p. diagrs., photos., tabs. 
(NACA RM L56E17) 



STATIC STABILITY CHARACTERISTICS OF A 
CAMBERED-DELTA-WING MODEL AT HIGH 
SUBSONIC SPEEDS. William C. Moseley, Jr. 
October 1956. 35 p. diagrs., photos. 
(NACA RM L56H13) 



EXPERIMENTAL AND PREDICTED LONGITUDINAL 
AND LATERAL -DIRECTIONAL RESPONSE CHAR- 
ACTERISTICS OF A LARGE FLEXIBLE 35° SWEPT- 
WING AIRPLANE AT AN ALTITUDE OF 35,000. FEET. 
Henry A. Cole, Jr., Stuart C. Brown, and Euclid C. 
Holleman. 1957. ii, 39p. diagrs., photo., tabs. 
(NACA Rept. 1330. Supersedes RM A54H09; 
TN 3874) 



AN ANALYSIS OF VERTICAL-TAIL LOADS MEAS- 
URED IN FLIGHT ON A SWEPT-WING BOMBER 
AIRP LANE . William A . McGowan and T . V . 
Cooney. May 1957. 53p. diagrs., photo., tabs. 
(NACARM L57B19) 



THE SUBSONIC STATIC AERODYNAMIC CHARAC- 
TERISTICS OF AN AIRPLANE MODEL HAVING A 
TRIANGULAR WING OF ASPECT RATIO 3. 
H - LATERAL AND DIRECTIONAL CHARACTERIS- 
TICS. Howard F. Savage and Bruce E. Tinling. 
August 1957. 82p. diagrs., photo., tabs. 
(NACA TN 4042. Supersedes RM A55B11) 



STATIC LONGITUDINAL AND LATERAL STABILITY 
CHARACTERISTICS AT LOW SPEED OF 45° 

SWEPTBACK-MIDWING MODELS HAVING WINGS 
WITH AN ASPECT RATIO OF 2, 4, OR 6. David F. 
Thomas, Jr., and Walter D. Woihart. September 
1957. 30p. diagrs., photos., tabs. (NACA TN 4077) 



151 



(1) AERODYNAMICS 



WIND-TUNNEL INVESTIGATION OF THE STATIC 
LATERAL STABILITY CHARACTERISTICS OF 
WING -FUSELAGE COMBINATIONS AT HIGH SUB- 
SONIC SPEEDS, TAPER-RATIO SERIES. James 
W. Wiggins and Paul G. Fournier. October 1957. 
25p. diagrs., photos. (NACA TN 4174. Supersedes 
RM L53B25a) 



EFFECT OF FLOW INCIDENCE AND REYNOLDS 
NUMBER ON LOW-SPEED AERODYNAMIC CHAR- 
ACTERISTICS OF SEVERAL NONCIRCULAR CYL- 
INDERS WITH APPLICATIONS TO DIRECTIONAL 
STABILITY AND SPINNING. Edward C. Polhamus. 
January 1958. 5*4p. diagrs., photo., tab. 
(NACA TN 4176) 



SUBSONIC FLIGHT INVESTIGATION OF METHODS 
TO IMPROVE THE DAMPING OF LATERAL OSCIL- 
LATIONS BY MEANS OF A VISCOUS DAMPER IN 
THE RUDDER SYSTEM IN CONJUNCTION WITH 
ADJUSTED HINGE-MOMENT PARAMETERS. 
Harold L. Crane, George J. Hurt, Jr., and 
John M. Elliott. January 1958. 45p. diagrs. , 
photos., tab. (NACA TN 4193. Supersedes 
RM L54D09) 



AERODYNAMIC RESEARCH ON FUSELAGES WITH 
RECTANGULAR CROSS SECTION. (Aerodynamische 
Untersuchungen an Rumpfen mit rechteckahnlichem 
Querschnitt.) K. Maruhn. July 1958. 37p. diagrs. 
(NACA TM 1414. Translation from Jahrbuch 19'42 
der 'dcutsch.cn Luftf ahrtforschung, p. 263 -279 . ) 



WIND-TUNNEL INVESTIGATION OF EFFECTS OF 
SPOILER LOCATION, SPOILER SIZE, AND FUSE- 
LAGE NOSE SHAPE ON DIRECTIONAL CHARACTER- 
ISTICS OF A MODEL OF A TANDEM -ROTOR HELI- 
COPTER FUSELAGE. James L. Williams. July 
1958. 44p. diagrs., photos., tab. (NACA TN 4305) 



LOW-SPEED EXPERIMENTAL DETERMINATION OF 
THE EFFECTS OF LEADING-EDGE RADIUS AND 
PROFILE THICKNESS ON STATIC AND OSCILLA- 
TORY LATERAL STABILITY DERIVATIVES FOR A 
DELTA WING WITH 60<> OF LEADING-EDGE SWEEP . 
Hermans. Fletcher. July 1958. 45p. diagrs. r 
photos., tabs. (NACA TN 4341) 



STATIC LONGITUDmAL AND LATERAL STABILITY 
CHARACTERISTICS AT LOW SPEED OF 60° 
SWEPTBACK-MIDWING MODELS HAVING WINGS 
WITH AN ASPECT RATIO OF 2, 4, OR 6. Walter D. 
Wolhart and David F. Thomas, Jr. September 1958. 
41p. diagrs., tabs. (NACA TN 4397) 



(1.8.1.2) 

DYNAMIC 



ESTIMATED TRANSONIC FLYING QUALITIES OF A 
TAILLESS AIRPLANE BASED ON A MODEL INVES- 
TIGATION. Charles J. Donlan and Richard E. Kuhn. 
June 8, 1949. 63p. diagrs., photos., tabs. 
(NACA RM L9D08) 



DERIVATION OF THE EQUATIONS OF MOTION OF 
A SYMMETRICAL WING- TIP -COUPLED AIRPLANE 
CONFIGURATION WITH ROTATIONAL FREEDOM 
AT THE JUNCTURES. Albert A. Schy. October 
1951. 4 5p. diagrs. (NACA RM L51G12) 



THEORETICAL INVESTIGATION OF THE PER- 
FORMANCE OF PROPORTIONAL NAVIGATION 
GUIDANCE SYSTEMS - EFFECT OF MISSILE CON- 
FIGURATION ON THE SPEED OF RESPONSE. 
Marvin Abramovitz. January 1953. 20p. diagrs., 
tabs. (NACA RM A52J22) 



DAMPING IN PITCH OF LOW-ASPECT-RATIO 
WINGS AT SUBSONIC AND SUPERSONIC SPEEDS. 
Murray Tobak. April 1953. ii, 107p. diagrs. 
(NACA RM A52L04a) 



A THEORETICAL STUDY OF THE EFFECT OF 
CONTROL -DE FLECTION AND CONTROL-RATE 
LIMITATIONS ON THE NORMAL ACCELERATION 
AND ROLL RESPONSE OF A SUPERSONIC INTER- 
CEPTOR. Howard F. Matthews and Stanley F. 
Schmidt. April 1953. 28p. photos., diaprs., 
tabs. (NACA RM A53B11) 



AN EXPERIMENTAL INVESTIGATION AT SUBSONIC 
AND SUPERSONIC SPEEDS OF THE TORSIONAL 
DAMPING CHARACTERISTICS OF A CONSTANT- 
CHORD CONTROL SURFACE OF AN ASPECT RATIO 
2 TRIANGULAR WING. David E. Reese, Jr. July 
1953. 32p. diagrs., photos., tab. 
(NACA RM A53D27) 



EFFECT OF AUTOMATIC STABILIZATION ON THE 
SIDESLIP AND ANGLE -OF -ATTACK DISTURBANCES 
IN ROLLING MANEUVERS. Ordway B. Gates, Jr., 
Joseph Weil, and C. H. Woodling. July 1955. 18p. 
diagrs. (NACA RM L55E25b) 



ANALYSIS OF EFFECTS OF AIRPLANE CHARAC- 
TERISTICS AND AUTOPDLOT PARAMETERS ON A 
ROLL-COMMAND SYSTEM WITH AILERON RATE 
AND DEFLECTION LIMITING. Albert A. Schy and 
Ordway B. Gates, Jr. September 1955. 68p. 
diagrs., tab. (NACA RM L55E18) 



ANALYSIS OF AN AUTOMATIC CONTROL TO PRE- 
VENT ROLLING DIVERGENCE . William H . 
Phillips. April 1956. 31p. diagrs., tab. 
(NACA RM L56A04) 



AN EVALUATION OF AN AEROMECHANICAL 
METHOD OF MINIMIZING SERVO-MJSSILE 
TRANSFER-FUNCTION VARIATIONS WITH FLIGHT 
CONDITION. Martin L. Nason. April 1956. 41p 
diagrs., tabs. (NACA RM L56A31) 



SOME NOTES ON THE VIOLENT LATERAL- 
LONGITUDINAL COUPLING MOTIONS OF THE 
DOUGLAS X-3 AIRPLANE IN AILERON ROLLS. 
Ralph W. Stone, Jr. May 1956. 35p. diagrs., tab. 
(NACA RM L56C15) 



AN ANALOG COMPUTER STUDY OF SEVERAL STA- 
BILITY AUGMENTATION SCHEMES DESIGNED TO 
ALLEVIATE ROLL-INDUCED INSTABILITY. Brent 
Y. Creer. February 1957. 50p. diagrs., tab. 
(NACA RM A56H30) 



STATUS OF SPIN RESEARCH FOR RECENT AIR- 
PLANE DESIGNS. Anshal I. Neihouse, Salter J. 
Klinar, and Stanley H. Scher. August 1957, ii, 
98p. diagrs., photos., tabs. (NACA RM L57F12) 



152 



(1) AERODYNAMICS 



MOTION OF A BALLISTIC MISSILE ANGULARLY 
MISALINED WITH THE FLIGHT PATH UPON EN- 
TERING THE ATMOSPHERE AND ITS EFFECT UP- 
ON AERODYNAMIC HEATING, AERODYNAMIC 
LOADS, AND MISS DISTANCE. H. Julian Allen. 
October 1957. 66p. diagrs., tabs. (NACA TN 4048. 
Supersedes RM A56F15) 



FLIGHT INVESTIGATION OF THE TRANSONIC 
LONGITUDINAL AND LATERAL HANDLING QUAL- 
ITIES OF THE- DOUGLAS X-3 RESEARCH AIRPLANE. 
Jack Fischel, Euclid C. Holleman, and Robert A. 
Tremant. December 1957. 61p. diagrs., photos., 
tab. (NACA RM H57I05) 



TRANSITION -FLIGHT INVESTIGATION OF A 
FOUR-ENGINE-TRANSPORT VERTICAL-TAKE- 
OFF AIRPLANE MODEL UTILIZING A LARGE 
FLAP AND EXTENSIBLE VANES FOR REDIRECT- 
ING THE PROPELLER SLIPSTREAM. Louis P. 
Tosti. December 1957. 35p. diagrs., photos., 
tab., film suppl. available on request. 
(NACA TN 4131) 



^i-8- 1-2. 1) 
Longitudinal 



WIND-TUNNEL INVESTIGATION OF THE STABILITY 
OF THE JETTISONABLE NOSE SECTION OF THE 
XS-2 AIRPLANE. Stanley H. Scher and Roscoe H. 
Goodwin. October 14, 1948. 19p. diagrs., photos., 
tabs. (NACA RM L8I14) 



INVESTIGATION OF THE DYNAMIC LATERAL 
STABILITY AND CONTROL CHARACTERISTICS OF 
A MODEL OF A FIGHTER AIRPLANE WITHOUT A 
HORIZONTAL TAn, AND EQUIPPED WITH EITHER 
SINGLE OR TWIN VERTICAL TAILS. John W. 
Draper and Robert W. Rose. November 15, 1949. 
20p. diagrs., photos., tab. (NACA RM L9J07a) 



PRELIMINARY RESULTS OF THE FLIGHT INVES- 
TIGATION BETWEEN MACH NUMBERS OF 0.80 AND 
1.36 OF A ROCKET -POWERED MODEL OF A 
SUPERSONIC AIRPLANE CONFIGURATION HAVING 
A TAPERED WING WITH CIRCULAR-ARC SECTIONS 
AND 40° SWEEPBACK. Charles T. D'Aiutolo and 
Homer P. Mason. October 31, 1950. 30p. diagrs., 
photos., tab. (NACA RM L50H29a) 



DETERMINATION OF LONGITUDINAL STABILITY 
OF THE BELL X-l AIRPLANE FROM TRANSIENT 
RESPONSES AT MACH NUMBERS UP TO 1.12 AT 
LIFT COEFFICIENTS OF 0.3 AND 0.6. Ellwyn E. 
Angle and Euclid C. Holleman. November 7, 1950. 
22p diagrs. (NACA RM L50I06a) 



AN INVESTIGATION OF THE LONGITUDINAL 
CHARACTERISTICS OF THE X-3 CONFIGURATION 
USING ROCKET -PROPELLED MODELS. PRELIMI- 
NARY RESULTS AT MACH NUMBERS FROM 0.65 
TO 1.25. Jesse L. Mitchell and Robert F. Peck. 
December 1, 1950, 30p. diagrs., photos. 
(NACA RM L50J03) 



WING -ON AND WING -OFF LONGITUDINAL CHAR- 
ACTERISTICS OF AN AIRPLANE CONFIGURATION 
HAVING A THIN UNSWEPT TAPERED WING OF 
ASPECT RATIO 3, AS OBTAINED FROM ROCKET- 
PROPELLED MODELS AT MACH NUMBERS FROM 
0.8 TO 1.4. Clarence L. Gillis and A. James Vitale. 
March 14, 1951. 52p. diagrs., photos,, tabs. 
(NACA RM L50K16) 



AN INVESTIGATION OF THE LONGITUDINAL CHAR- 
ACTERISTICS OF THE X-3 CONFIGURATION WITH 
WING AND HORIZONTAL TAIL SURFACES OF 
ASPECT RATIO 3.0 BY MEANS OF ROCKET- 
PROPELLED MODELS. RESULTS AT HIGH LIFT 
COEFFICIENTS. Robert F. Peck and Jesse L. 
Mitchell. August 27, 1951. 34p. diagrs., photos. 
(NACA RM L51G10) 



FLIGHT DETERMINATION OF THE DRAG AND 
LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A ROCKET -POWERED MODEL 
OF A 60° DELTA-WING AIRPLANE FROM MACH 
NUMBERS OF 0.75 TO 1.70. Grady L. Mitcham, 
Norman L. Crabill, and Joseph E. Stevens. 
November 1951. 44p. diagrs., photos., tab. 
(NACA RM L51I04) 



THE EFFECT OF VARIOUS MISSILE CHARACTER- 
ISTICS ON AIRFRAME FREQUENCY RESPONSE. 
Howard F. Matthews and Walter E. McNeill. 
January 1952. 16p. diagrs. (NACA RM A51L17a) 



THE STATIC AND DYNAMIC LONGITUDINAL STA- 
BILITY CHARACTERISTICS OF SOME SUPERSONIC 
AIRCRAFT CONFIGURATIONS. Jesse L. Mitchell. 
January 1952. 19p. diagrs. (NACA RM L52A10a) 



LONGITUDINAL STABILITY AND DRAG CHARAC- 
TERISTICS AT MACH NUMBERS FROM 0.75 TO 1.5 
OF AN AIRPLANE CONFIGURATION HAVING A 60° 
SWEPT WING OF ASPECT RATIO 2.24 AS OB- 
TAINED FROM ROCKET-PROPELLED MODELS. 
A. James Vitale, John C. McFall, Jr., and John D. 
Morrow. April 1952. 43p. diagrs., photos., tabs. 
(NACA RM L51K06) 



LONGITUDINAL AERODYNAMIC CHARACTERISTICS 
OF MODEL AIRPLANE CONFIGURATION EQUTPPED 
WITH A SCALED X-l AIRPLANE WING. James H. 
Parks. April 1952. 37p. diagrs. 
(NACA RM L5lLl0a) 



PRELIMINARY INVESTIGATION OF THE LOW- 
AMPLITUDE DAMPING IN PITCH OF TAILLESS 
DELTA- AND SWEPT-WING CONFIGURATIONS AT 
MACH NUMBERS FROM 0.7 TO 1.35. Charles T. 
D'Aiutolo and Robert N. Parker. August 1952. 27p. 
diagrs. Kjphotos., tab. (NACA RM L52G09) 



LONGITUDINAL STABILITY, CONTROL EFFEC- 
TIVENESS, AND DRAG CHARACTERISTICS AT 
TRANSONIC SPEEDS OF A ROCKET -PROPELLED 
MODEL OF AN AIRPLANE CONFIGURATION 
HAVING AN UNSWEPT TAPERED WING OF ASPECT 
RATIO 3.0 AND NACA 65A004.5 AIRFOIL SECTIONS. 
JohnC. McFall, Jr., and James A. Hollinger. 
January 1953. 30p. diagrs., photos. 
(NACA RM L52L04) 



STABILITY OF BODIES OF REVOLUTION HAVING 
FINENESS RATIOS SMALLER THAN 1.0 AND 
HAVING ROUNDED FRONTS AND BLUNT BASES- 
Stanley H- Scher and James S. Bowman, Jr. 
January 1953. 23p. diagrs., tabs. 
(NACA RM L52L08) 



DAMPING IN PITCH OF LOW-ASPECT-RATIO 
WINGS AT SUBSONIC AND SUPERSONIC SPEEDS. 
Murray Tobak. April 1953. ii, 107p. diagrs. 
(NACA RM A52L04a) 



( 1 ) AERODYNAMICS 



153 



A ROCKET-MODEL INVESTIGATION OF THE LON- 
GITUDINAL STABILITY, LIFT, AND DRAG CHAR- 
ACTERISTICS OF THE DOUGLAS X-3 CONFIGURA- 
TION WITH HORIZONTAL TAIL OF ASPECT RATIO 
4.33. Robert F. Peck and James A. Hollinger. 
August 1953. 33p. diagrs., photos. 
(NACA RM L53F19a) 



THEORETICAL CALCULATIONS OF THE STABILI- 
TY DERIVATIVES AT SUPERSONIC SPEEDS FOR A 
HIGH-SPEED AIRPLANE CONFIGURATION. 
Kenneth Margolis and Percy J. Bobbitt. October 
1953. 59p. diagrs., tab. (NACA RM L53G17) 



A FLIGHT INVESTIGATION AT MACH NUMBERS 
FROM 0.67 TO 1.61 OF THE LONGITUDINAL 
STABILITY AND CONTROL CHARACTERISTICS OF 
A 60° DELTA- WING MISSILE CONFIGURATION 
HAVING AN ALL-MOVABLE TAIL, Martin T. 
Moul and Hal T. Baber, Jr. October 1953. 43p. 
diagrs., photo. (NACA RM L53G29) 



INVESTIGATION AT MACH NUMBERS OF 1 62. 1 .93, 
AND 2.41 OF THE EFFECT OF OSCILLATION 
AMPLITUDE ON THE DAMPING IN PITCH OF 
DELTA-WING -BODY COMBINATIONS. Arthur 
Henderson, Jr. October 1953. 28p. diagrs.. 
photos. (NACA RM L53H25) 



THE INTERPRETATION OF NONLINEAR PITCHING 
MOMENTS IN RELATION TO THE PITCH-UP 
PROBLEM. George S. Campbell and Joseph Weil. 
October 1953. 32p. diagrs., tabs. 
(NACA RM L53I02) 



FLIGHT MEASUREMENTS OF THE HORIZONTAL- 
TAIL LOADS ON A SWEPT-WING FIGHTER AIR- 
PLANE AT TRANSONIC SPEEDS. Melvin Sadoff. 
November 1953. 58p. diagrs., photo., tab. 
(NACA RM A53G10) 



AERODYNAMIC CHARACTERISTICS AT TRANSONIC 
AND SUPERSONIC SPEEDS OF A ROCKET- 
PROPELLED AIRPLANE CONFIGURATION HAVING 
A 52.50 DELTA WING AND A LOW, SWEPT HORI- 
ZONTAL TAIL. AlanB. Kehlet. March 1954. 31p. 
.diagrs., photos. (NACA RM L54A20) 



ROCKET-POWERED MODEL INVESTIGATION OF 
LIFT, DRAG, AND STABILITY OF A BODY -TAIL 
CONFIGURATION AT MACH NUMBERS FROM 0.8 
TO 2.3 AND ANGLES OF ATTACK BETWEEN ±6.5<>. 
Warren Gillespie, Jr., and Albert E. Dletz. April 
1954. 42p. diagrs., photos., tabs. 
(NACA RM L54C04) 



LOW-AMPLITUDE DAMP ING-IN- PITCH CHARAC- 
TERISTICS OF TAILLESS DELTA -WING- BODY 
COMBINATIONS AT MACH NUMBERS FROM 0.80 
TO 1.35 AS OBTAINED WITH ROCKET-POWERED 
MODELS. Charles T. D'Aiutolo. June 1954. 34p. 
diagrs., photos., tab. (NACA RM L54D29) 



A FLIGHT INVESTIGATION AT TRANSONIC SPEEDS 
OF THE AERODYNAMIC CHARACTERISTICS OF A 
MODEL HAVING A THIN UNSWEPT WING OF 
ASPECT RATIO 3.1. Maurice D. White. August 
1954. 41p. diagrs., photo., tabs. 
(NACA RM A54E12) 



AERODYNAMIC CHARACTERISTICS AT TRANSONIC 
AND SUPERSONIC SPEEDS OF A ROCKET- 
PROPELLED AIRPLANE CONFIGURATION HAVING 
A DIAMOND- PLAN- FORM WING OF ASPECT RATIO 
3.08 AND A LOW, SWEPT HORIZONTAL TAIL. 
Alan B. Kehlet. September 1954. 37p. diagrs., 
photos. (NACA RM L54G27a) 



ANALYTICAL STUDY OF THE EFFECT OF 
CENTER-OF-GRAVITY POSITION ON THE RE- 
SPONSE TO LONGITUDINAL CONTROL IN LANDING 
APPROACHES OF A SWEPT-WING AIRPLANE OF 
LOW ASPECT RATIO HAVING NO HORIZONTAL 
TAIL. Ralph W. Stone, Jr. October 1954. 35p. 
diagrs., tabs. (NACA RM L54H04) 



LOW-AMPLITUDE DAMPING-IN-PITCH CHARAC- 
TERISTICS OF FOUR TAILLESS SWEPT WING- 
BODY COMBINATIONS AT MACH NUMBERS FROM 
0.85 TO 1.30 AS OBTAINED WITH ROCKET- 
POWERED MODELS. Charles T. D'Aiutolo. 
November 1954. 34p. diagrs., photos., tab. 
(NACA RM L54I10) 



A FLIGHT INVESTIGATION AT TRANSONIC 
SPEEDS AND SMALL ANGLES OF ATTACK OF THE 
AERODYNAMIC CHARACTERISTICS OF A MODEL 
HAVING A 450 SWEPTBACK WING OF ASPECT 
RATIO 3 WITH AN NACA 64A006 AIRFOIL SECTION. 
George H. Holdaway. January 1955. 32p. diagrs., 
photo., tab. (NACA RM A54I17) 



TRANSONIC LONGITUDINAL AERODYNAMIC 
EFFECTS OF SWEEPING UP THE REAR OF THE 
FUSELAGE OF A ROCKET-PROPELLED AIR- 
PLANE MODEL HAVING NO HORIZONTAL TAIL. 
James H. Parks. January 1955. 30p. diagrs., 
photo. (NACA RM L54K12) 



FLIGHT EXPERIENCE WITH TWO HIGH-SPEED 
AIRPLANES HAVING VIOLENT LATERAL- 
LONGITUDINAL COUPLING IN AILERON ROLLS. 
NACA High-Speed Flight Station. February 1955. 
30p. diagrs., photos., tabs. (NACA RM H55A13) 



A FLIGHT INVESTIGATION AT TRANSONIC SPEEDS 
OF A MODEL HAVING A TRIANGULAR WING OF 
ASPECT RATIO 4. Loren G. Bright. March 1955. 
40p. diagrs., photos., tabs. (NACA RM A54L27) 



A THEORETICAL INVESTIGATION OF THE EF- 
FECT OF AUXILIARY DAMPING ON THE LONGI- 
TUDINAL RESPONSE OF A TRANSONIC BOMBER 
CONFIGURATION IN FLIGHT THROUGH CON- 
TINUOUS TURBULENCE. T. F. Bridgland, Jr 
March 1955. 26p. diagrs., tab. 
(NACA RML54K15a) 



STUDY OF SOME EFFECTS OF STRUCTURAL 
FLEXIBILITY ON THE LONGITUDINAL MOTIONS 
AND LOADS AS OBTAINED FROM FLIGHT MEAS- 
UREMENTS OF A SWEPT-WING BOMBER. James 
J. Donegan and Carl R. Huss. May 1955. 53p. 
diagrs., tabs. (NACA RM L54L16) 



FLIGHT EXPERIENCE OF INERTIA COUPLING IN 
ROLLING MANEUVERS. Joseph Weil, Ordway B. 
Gates, Jr., Richard D. Banner, and Albert E. Kuhl. 
July 1955. 12p. diagrs. (NACA RM H55E17b) 



154 



( 1 ) AERODYNAMICS 



A FLIGHT INVESTIGATION AT TRANSONIC SPEEDS 
OF A MODEL HAVING A TRIANGULAR WING OF 
ASPECT RATIO 2. Maurice D. White. September 
1955. 39p. diagrs., photo.,' tabs. 
(NACA RM A55F21) 



FREE-FLIGHT INVESTIGATION TO OBTAIN DRAG- 
AT-LIFT AND STABILITY DATA FOR A 60° DELTA- 
WING-BODY CONFIGURATION OVER A MACH NUM- 
BER RANGE OF 1.3 TO 1.6. Clement J. Welsh. 
October 1955. 23p. diagrs., photo., tab. 
(NACA RM L55G14) 



A THEORETICAL ANALYSIS OF A SIMPLE AERO- 
DYNAMIC DEVICE TO IMPROVE THE LONGITUDI- 
NAL DAMPING OF A CRUCIFORM MISSILE CON- 
FIGURATION AT SUPERSONIC SPEEDS. James E. 
Clements. October 1955. 36p. diagrs., tab. 
(NACA RM L55H31) 



EXPERIMENTAL RESULTS FROM A TEST IN 
ROUGH AIR AT HIGH SUBSONIC SPEEDS OF A 
TAILLESS ROCKET MODEL HAVING CRUCIFORM 
TRIANGULAR WINGS, AND A NOTE ON THE CAL- 
CULATION OF MEAN SQUARE LOADS OF AIR- 
CRAFT IN CONTINUOUS ROUGH ATR. A- James 
Vitale and Jesse L. Mitchell. April 1956. 25p. 
diagrs., photo., tab. (NACA RM L55L28) 



LATERAL STABILITY CHARACTERISTICS BE- 
TWEEN MACH NUMBERS OF 0.80 AND 1.57 AND 
SIMULATION OF COUPLED MOTION AT MACH 
NUMBER 1.30 OF A ROCKET-PROPELLED MODEL 
OF AN AIRPLANE CONFIGURATION HAVING THIN 
HIGHLY TAPERED 45° SWEPTBACK SURFACES. 
Charles T. D'Aiutolo and Allen B. Henning. April 
1956. 41p. diagrs., photos., tabs. 
(NACA RM L56A17) 



AN EVALUATION OF AN AEROMECHANICAL 
METHOD OF MINIMIZING SERVO-MISSILE 
TRANSFER-FUNCTION VARIATIONS WITH FLIGHT 
CONDITION. Martin L. Nason. April 1956. 41p. 
diagrs., tabs. (NACA RM L56A31) 



RESULTS FROM AN INVESTIGATION IN ROUGH 
AIR AT MACH NUMBERS FROM 0.84 TO 1.67 OF A 
TAILLESS ROCKET MODEL HAVING 60° TRIANGU- 
LAR WINGS. A. James Vitale. July 1956 I6p. 
diagrs., photo., tab. (NACA RM L56F07a) 



DYNAMIC MODEL INVESTIGATION OF TWO TAIL- 
SITTER VERTICALLY RISING AIRPLANES TO DE- 
TERMINE THE ALTITUDE REQUIRED TO AP- 
PROACH NORMAL-FLK3HT CONDITIONS AFTER 
POWER F ADJURE IN HOVERING FLIGHT. Walter 
J. Klinar and L. Faye Wilkes. November 1956. 
15p. diacrrs., tabs. (NACA RM L56H29a) 



EXPERIMENTAL AND PREDICTED LONGITUDINAL 
AND LATERAL-DIRECTIONAL RESPONSE CHAR- 
ACTERISTICS OF A LARGE FLEXIBLE 35° SWEPT - 
WING AIRPLANE AT AN ALTITUDE OF 35,000 FEET. 
Henry A. Cole, Jr., Stuart C. Brown, and Euclid C. 
Holleman. 1957. ii, 39p. diagrs., photo., tabs. 
(NACA Rept. 1330. Supersedes RM A54H09; 
TN 3874) 



DETERMINATION OF LONGITUDINAL STABILITY 
AND CONTROL CHARACTERISTICS FROM FREE- 
FLIGHT MODEL TESTS WITH RESULTS AT TRAN- 
SONIC SPEEDS FOR THREE AIRPLANE CONFIGU- 
RATIONS. Clarence L. Gillis and Jesse L. Mitchell 
1957. Ii, 28p diagrs., photos., tabs. 
(NACA Rept. 1337) 



HORIZONTAL-TAIL PARAMETERS AS DETER- 
MINED FROM FLIGHT -TEST TAIL LOADS ON A 
FLEXIBLE SWEPT-WING JET BOMBER. William 
S. Aiken, Jr., and Raymond A. Fisher. January 
1957. 42p. diagrs., photos., tabs. 
(NACA RM L56J02) 



FLIGHT -TEST INVESTIGATION ON THE LANGLEY 
CONTROL-LINE FACILITY OF A MODEL OF A 
PROPELLER-DRIVEN TAIL-SITTER-TYPE 
VERTICAL-TAKE-OFF AIRPLANE WITH DELTA 
WING DURING RAPID TRANSITIONS. Robert O. 
Schade. August 1957. 19p. diagrs., photo., tab. 
(NACA TN 4070) 



ON THE MINIMIZATION OF AIRPLANE RESPONSES 
TO RANDOM GUSTS. Murray Tobak. October 
1957. 71p. diagrs. (NACA TN 3290) 



AN ANALYTICAL INVESTIGATION OF THE GUST- 
ALLEVIATING PROPERTIES OF A SIMPLE PITCH 
DAMPER. Norman L. Crabill. December 1957. 
47p. diagrs., tab. (NACA TN 4173) 



THREE-DEGREE-OF-FREEDOM EVALUATION 
OF THE LONGITUDINAL TRANSFER FUNCTIONS 
OF A SUPERSONIC CANARD MISSILE CONFIGU- 
RATION INCLUDING CHANGES IN FORWARD 
SPEED. Ernest C. Seaberg. December 1957. 
29p. diagrs., photo., tabs. (NACA TN 4192. 
Supersedes RM L54C02) 



A SIMPLIFIED METHOD FOR APPROXIMATING 
THE TRANSIENT MOTION IN ANGLES OF ATTACK 
AND SIDESLD? DURING A CONSTANT ROLLING 
MANEUVER. Leonard Stemfield. 1958. ii, lip. 
diagrs., tabs. (NACA Rept. 1344. Supersedes 
RM L56F04) 



MEASURED AND PREDICTED DYNAMIC RESPONSE 
CHARACTERISTICS OF A FLEXIBLE AIRPLANE TO 
ELEVATOR CONTROL OVER A FREQUENCY RANGE 
INCLUDING THREE STRUCTURAL MODES. 
Henry A. Cole, Jr., and Euclid C. Holleman. 
February 1958. 81p. diagrs., photo., tabs. 
(NACA TN 4147) 



QUALITATIVE SIMULATOR STUDY OF LONGITU- 
DINAL STICK FORCES AND DISPLACEMENTS 
DESIRABLE DURING TRACKING. Stanley Faber. 
February 1958. 23p. diagrs., photo. 
(NACA TN 4202) 



A THEORETICAL ANALYSIS OF THE EFFECT OF 
ENGINE ANGULAR MOMENTUM ON LONGITUDINAL 
AND DIRECTIONAL STABILITY IN STEADY ROLL- 
ING MANEUVERS. Ordway B. Gates, Jr., and 
C. H. Woodling. April 1958. 20p. diagrs., tab. 
(NACA TN 4249. Supersedes RM L55G05> 



WIND-TUNNEL INVESTIGATION AT LOW SPEEDS 
OF FLIGHT CHARACTERISTICS OF A SWEPTBACK- 
WING JET-TRANSPORT AIRPLANE MODEL 
EQWPPED WITH AN EXTERNAL-FLOW JET- 
AUGMENTED SLOTTED FLAP. Joseph L. Johnson, 
Jr. July 1958. 32p. diagrs., photos., tab., film 
suppl. available on request. (NACA TN 4255) 



DYNAMIC STABILITY OF VEHICLES TRAVERSING 
ASCENDING OR DESCENDING PATHS THROUGH 
THE ATMOSPHERE. Murray Tobak and H. Julian 
Allen. July 1958. (i), 35p. diagrs. 
(NACA TN 4275) 



155 



(1) AERODYNAMICS 



MEASUREMENTS OF THE MOTIONS OF A LARGE 
SWEPT -WING AIRPLANE IN ROUGH AIR. Richard 
H. Rhyne. September 1958. 22p. diagrs., photo., 
tabs. (NACA TN 4S10) 



APPROXIMATE METHOD FOR CALCULATING 
MOTIONS IN ANGLES OF ATTACK AND SIDESLIP 
DUE TO STEP PITCHING- AND YAWING-MOMENT 
INPUTS DURING STEADY ROLL Martin T. Moul 
and Teresa R. Brennan. September 1958. 42p. 
diagrs., tabs. (NACA TN 4346) 



(1.8.1.2.2) 
Lateral and Directional 



WIND-TUNNEL INVESTIGATION OF THE STABILITY 
OF THE JETTISONABLE NOSE SECTION OF THE 
XS-2 AIRPLANE. Stanley H. Scher and Roscoe H . 
Goodwin. October 14, 1948. 19p. diagrs., photos., 
tabs. (NACA RM L8I14) 



ANALYSIS OF THE DYNAMIC-LATERAL-STABILITY 
CHARACTERISTICS OF THE BELL X-2 AIRPLANE 
AS AFFECTED BY VARIATIONS IN MASS, AERO- 
DYNAMIC, AND DIMENSIONAL PARAMETERS. 
W. H. Michael, Jr., and M, J. Queijo. August 10, 
194S. 33p. diagrs., tabs. (NACA RM L9G13) 



FLIGHT TESTS OF A MODEL HAVING SELF- 
SUPPORTING FUEL-CARRYING PANELS HINGED 
TO THE WING TIPS. Robert E. Shanks and David C 
Grana. November 2, 1949. lOp. diagrs., tab. 
(NACA RM L9I07a) 



INVESTIGATION OF THE DYNAMIC LATERAL 
STABILITY AND CONTROL CHARACTERISTICS OF 
A MODEL OF A FIGHTER AIRPLANE WITHOUT A 
HORIZONTAL TAIL AND EQUIPPED WITH EITHER 
SINGLE OR TWIN VERTICAL TAILS. John W. 
Draper and Robert W. Rose. November 15, 1949. 
20p. diagrs., photos., tab. (NACA RM L9J07a) 



SUPPLEMENTARY ANALYSIS OF THE DYNAMIC 
LATERAL STABILITY CHARACTERISTICS OF THE 
BELL X-2 AIRPLANE AS AFFECTED BY VARIA- 
TIONS IN MASS AND AERODYNAMIC PARAMETERS. 
William H. Michael, Jr., andM. J. Queijo. 
June 26, 1950. 15p. diagrs. (NACA RM L50E08) 



A PRELIMINARY FLIGHT INVESTIGATION OF THE 
EFFECT OF SNAKING OSCILLATIONS ON THE 
PILOTS* OPINIONS OF THE FLYING QUALITIES OF 
A FIGHTER AIRPLANE. Arnold R. Beckhardt, 
John A. Harper, and William L. AUord. * 
September 26, 1950. 31p. diagrs., photos., tabs. 
(NACA RM L50E17a) 



AN INVESTIGATION OF SINGLE -DEGREE -OF- 
FREEDOM SNAKING OSCILLATIONS ON A MODEL 
OF A HIGH-SPEED RESEARCH AIRPLANE BY THE 
NACA WING-FLOW METHOD. Harold I. Johnson 
and Stanley Faber. August 1951. 22p. diagrs., 
photos., tab. (NACA RM L51E14) 



FREE-FLIGHT -TUNNEL INVESTIGATION OF THE 
DYNAMIC LATERAL STABILITY AND CONTROL 
CHARACTERISTICS OF A HIGH-ASPECT-RATIO 
BOMBER MODEL WITH SELF-SUPPORTING FREE- 
FLOATING FUEL TANKS ATTACHED TO THE WING 
TIPS. Charles V. Bennett and Robert B. Cadman. 
August 1951. I2p. diagrs., tab. (NACA RM L51E17) 



FREE -FLIGHT -TUNNEL INVESTIGATION OF THE 
DYNAMIC LATERAL STABILITY AND CONTROL 
CHARACTERISTICS OF A HIGH-ASPECT -RATIO 
BOMBER MODEL WITH A SWEPTBACK-WING 
FIGHTER MODEL ATTACHED TO EACH WTNG TIP. 
Charles V. Bennett and Peter C. Boisseau. 
September 1952. 17p. diagrs., tabs. 
(NACA RM L52E08) 



SOME MEASUREMENTS OF FLYING QUALITIES OF 
A DOUGLAS D-558-II RESEARCH AIRPLANE DUR- 
ING FLIGHTS TO SUPERSONIC SPEEDS. Herman O. 
Ankenbruck and Theodore E. Dahlen. March 1953. 
25p. diagrs., photos., tab. (NACA RM L53A06) 



A STUDY OF VISUAL INTERCEPTION ATTACKS 
ON A NONMANEUVERTNG AIRPLANE TARGET. 
Donald C. Cheatham, Charles W. Mathews, and 
John A. Harper. July 1953. 97 p. diagrs., photos., 
tabs. (NACA RM L53E01) 



THEORETICAL CALCULATIONS OF THE STABILI- 
TY DERIVATIVES AT SUPERSONIC SPEEDS FOR A 
HIGH-SPEED AIRPLANE CONFIGURATION. 
Kenneth Margolls and Percy J. Bobbitt. October 
1953. 59p. diagrs., tab. (NACA RM L53G17) 



STABILITY AND DRAG CHARACTERISTICS AT 
MACH NUMBERS FROM 0.8 TO 1.5 OF A FREE- 
FLIGHT MODEL HAVING 3-PERCENT-THICK, 60<> 
TRIANGULAR WING AND HORIZONTAL TAIL SUR- 
FACES. Rowe Chapman, Jr., and H array A. 
Wallskog. August 1954. 3 Op. diagrs., photos., tab. 
(NACA RM L54G23a) 



LATERAL MOTIONS ENCOUNTERED WITH THE 
DOUGLAS D-558-II ALL-ROCKET RESEARCH AIR- 
PLANE DURING EXPLORATORY FLIGHTS TO A 
MACH NUMBER OF 2.0. Herman O. Ankenbruck 
and Chester H. Wolowicz. December 1954. 32p. 
diagrs., photos., tab. (NACA RM H54I27) 



JET EFFECTS ON LONGITUDINAL TRIM OF AN 
AIRPLANE CONFIGURATION MEASURED AT MACH 
NUMBERS BETWEEN 1.2 AND 1.8. Robert F. Peck. 
January 1955. 17p. diagrs., photos. 
(NACA RML54J 29a) 



FLIGHT EXPERIENCE WITH TWO HIGH-SPEED 
AIRPLANES HAVING VIOLENT LATERAL - 
LONGITUDINAL COUPLING IN AILERON ROLLS. 
NACA High-Speed Flight Station. February 1955. 
30p. diagrs., photos., tabs. (NACA RM H55A13) 



INVESTIGATION OF THE LATERAL STABILITY 
CHARACTERISTICS OF THE DOUGLAS X-3 CON- 
FIGURATION AT MACH NUMBERS FROM 0.8 TO 
1.1 BY MEANS OF A ROCKET -PROPELLED 
MODEL. Jesse L. Mitchell and Robert F. Peck. 
February 1955. 37p. diagrs., photo., tabs. 
(NACA RM L54L20) 



LATERAL STABILITY CHARACTERISTICS AT LOW 
LIFT BETWEEN MACH NUMBERS OF 0.85 AND 1.15 
OF A ROCKET-PROPELLED MODEL OF A SUPER- 
SONIC AIRPLANE CONFIGURATION HAVRJG A 
TAPERED WING WITH CIRCULAR-ARC SECTIONS 
AND 40° SWEEPBACK. Charles T. D'Aiutolo and 
Allen B. Henning. April 1955. 50p. diagrs., 
photos., tabs. (NACA RM L55A31) 



156 



( 1 ) AERODYNAMICS 



LATERAL STABILITY AND CONTROL CHARACTER- 
ISTICS OF THE CONVAIR XF-92A DELTA-WING 
AIRPLANE AS MEASURED IN FLIGHT. Thomas R. 
Sisk and Duane O. Muhleman. May 1955. 55p. 
diagrs., photos,, tabs. (NACA RM H55A17) 



FLIGHT EXPERIENCE OF INERTIA COUPLING IN 
ROLLING MANEUVERS. Joseph Weil, Ordway B. 
Gates, Jr., Richard D. Banner, and Albert E. Kuhl. 
July 1955. I2p. diagrs. (NACA RM H55E17b) 



EFFECT OF SEVERAL WING MODIFICATIONS ON 
THE LOW-SPEED STALLING CHARACTERISTICS OF 
THE DOUGLAS D-558-II RESEARCH AIRPLANE. 
Jack Fischel and Donald Reisert. July 1955. 62p. 
diagrs., photos., tabs. (NACA RM H55E31a) 



A THEORETICAL INVESTIGATION OF A COMPEN- 
SATJNG NETWORK WITH APPLICATION TO ROLL 
CONTROL SYSTEMS FOR AUTOMATIC INTERCEP- 
TORS. Windsor L. Sherman. July 1955. 64p. 
diagrs-, tab. (NACA RM L55E20) 



FLIGHT MEASUREMENTS OF THE LATERAL 
RESPONSE CHARACTERISTICS OF THE CONVAIR 
XF-92A DELTA-WING AIRPLANE. Euclid C. 
Holleman. August 1955. 37p. diagrs., tabs. 
(NACA RM H55F.*rt 



FLIGHT MEASUREMENTS OF DIRECTIONAL STA- 
BILITY TO A MACH NUMBER OF 1.48 FOR AN 
AIRPLANE TESTED WITH THREE DIFFERENT 
VERTICAL TAIL CONFIGURATIONS. Hubert M. 
Drake, Thomas W. Finch, and James R. Peele. r 
October 1955. 22p. diagrs., photos., tab. 
(NACA RM H55G26) 



WIND-TUNNEL MEASUREMENTS OF THE DYNAMIC 
CROSS DERIVATIVE C, - C, . (ROLLING MO- 

MENT DUE TO YAWING VELOCITY AND TO AC- 
CELERATION IN SIDESLIP) OF THE DOUGLAS 
D-558-U AIRPLANE AND ITS COMPONENTS AT 
SUPERSONIC SPEEDS INCLUDING DESCRIPTION 
OF THE TECHNIQUE. William B. Boatright. 
November 1955. 57p. diagrs., photos. 
(NACARM L55H16) 



EXPERIMENTAL INVESTIGATION AT HIGH SUB- 
SONIC SPEED OF THE ROLLING STABILITY 
DERIVATIVES OF A COMPLETE MODEL HAVING 
A CLIPPED-DELTA WING AND A HIGH HORIZON- 
TAL TAIL. William C. Sleeman, Jr., and Albert G. 
Few, Jr. February 1956. 32p. diagrs., tab. 
fNACA RM L55K11) 



SPINNING AND RELATED PROBLEMS AT HIGH 
ANGLES OF ATTACK FOR HIGH-SPEED AIR- 
PLANES. Walter J, Klinar. March 1956. 8p. 
diagrs. (NACA RM L55L23a) 



AN ANALOG STUDY OF THE RELATIVE IMPOR- 
TANCE OF VARIOUS FACTORS AFFECTING ROLL 
COUPLING. Joseph Weil and Richard E Day. 
April 1956. 81p. diagrs., photo., tabs. 
(NACA RM H56A06) 



LATERAL STABILITY CHARACTERISTICS BE- 
TWEEN MACH NUMBERS OF 0.80 AND 1.57 AND 
SIMULATION OF COUPLED MOTION AT MACH 
NUMBER 1.30 OF A ROCKET-PROPELLED MODEL 
OF AN AIRPLANE CONFIGURATION HAVING THIN 
HIGHLY TAPERED 45° SWEPTBACK SURFACES. 
Charles T. D'Aiutolo and Allen B. Henning. April 
1956. 41p. diagrs., photos., tabs. 
(NACA RM L56A17) 



SOME EFFECTS OF WING FENCES ON THE LATER- 
AL STABILITY DERIVATIVES OF A 60° DELTA 
WING OSCILLATING CONTINUOUSLY IN YAW. 
Donald R. Riley. July 1956. 29p. diagrs., photos., 
tab. (NACA RM L56D13) 



EFFECT OF WING HEIGHT AND DIHEDRAL ON THE 
LATERAL STABILITY CHARACTERISTICS AT LOW 
LIFT OF A 45° SWEPT -WING AIRPLANE CONFIG- 
URATION AS OBTAINED FROM TIME-VECTOR 
ANALYSES OF ROCKET -PROPELLED-MODEL 
FLIGHTS AT MACH NUMBERS FROM 0.7 TO 1.3. 
Clarence L. Gillis and Rowe Chapman, Jr. 
September 1956. 70p. diagrs., photos., tabs. 
(NACA RM L56E17) 



LOW -SPEED MEASUREMENT OF TAIL CONTRI- 
BUTION TO ROLLING STABILITY DERIVATIVES 
AND AIR-FLOW ANGULARITY AT THE TAIL FOR 
AN X-TAIL MODEL IN STEADY ROLL INCLUDING 
SOME EFFECTS OF WING-TIP STORES. Donald R. 
Riley. November 1956. 28p. diagrs., photo., tab. 
(NACA RM L56I21) 



LINEARIZED LIFTING-SURFACE AND LIFTING- 
LINE EVALUATIONS OF SIDEWASH BEHIND ROLL- 
ING TRIANGULAR WINGS AT SUPERSONIC SPEEDS. 
Percy J. Bobbitt. 1957. 11, 19p. diagrs., photo. 
(NACA Kept. 1301. Supersedes TN 3609) 



FUIGHT INVESTIGATION OF THE EFFECTIVENESS 
OF AN AUTOMATIC AILERON TRIM CONTROL 
DEVICE FOR PERSONAL AIRPLANES. William H. 
Phillips, Helmut A. Kuehnel, and James B. Whitten. 
1957. ii, 15p. diagrs., photos. 
(NACA Rept. 1304, Supersedes TN 3637) 



THEORETICAL CALCULATION OF THE POWER 
SPECTRA OF THE ROLLING AND YAWING 
MOMENTS ON A WING IN RANDOM TURBULENCE. 
John M. Eggleston and Franklin W. Diederich. 
1957. ii, I9p. diagrs., tabs. (NACA Rept. 1321. 
Supersedes TN 3864.) 



EXPERIMENTAL DETERMINATION AT SUBSONIC 
SPEEDS OF THE OSCILLATORY AND STATIC 
LATERAL STABILITY DERIVATIVES OF A SERxcS 
OF DELTA WINGS WITH LEADING-EDGE SWEEP 
FROM 30° TO 86.5°. William Letko. April 1957. 
38p. diagrs., photos., tab. (NACA RM L57A30) 



A METHOD UTILIZING DATA ON THE SPIRAL, 
ROLL-SUBSIDENCE, AND DUTCH ROLL MODES 
FOR DETERMINING LATERAL STABILITY DERIV- 
ATIVES FROM FLIGHT MEASUREMENTS. Bernard 
B. Klawans and Jack A. White. August 1957. 38p. 
diagrs., tabs. (NACA TN 4066) 



( 1 ) AERODYNAMICS 



157 



EFFECT OF FREQUENCY OF SIDESLIPPING 
MOTION ON THE LATERAL STABILITY DERIVA- 
TIVES OF A TYPICAL DELTA-WING AIRPLANE. 
Jacob H. Lichtenstein and James L. Williams. 
September 1957. 46p. diagrs., photos., tabs. 
(NACA RM L57F07) 



WIND-TUNNEL INVESTIGATION OF EFFECTS OF 
GROUND PROXIMITY AND OF SPLIT FLAPS ON 
THE LATERAL STABILITY DERIVATIVES OF A 60° 
DELTA-WING MODEL OSCILLATING IN YAW. 
Byron M. Jaquet. September 1957. 32p. diagrs. 
photos., tab. (NACA TN 4119) 



A SIMPLIFIED METHOD FOR APPROXIMATING 
THE TRANSIENT MOTION IN ANGLES OF ATTACK 
AND SIDESLIP DURING A CONSTANT ROLLING 
MANEUVER. Leonard Sternfield. 1958. ii, lip. 
diagrs., tabs. (NACA Rept. 1344. Supersedes 
RM L56F04) 



SUBSONIC FLIGHT INVESTIGATION OF METHODS 
TO IMPROVE THE DAMPING OF LATERAL OSCIL- 
LATIONS BY MEANS OF A VISCOUS DAMPER IN 
THE RUDDER SYSTEM IN CONJUNCTION WITH 
ADJUSTED HINGE-MOMENT PARAMETERS, 
Harold L. Crane, George J. Hurt, Jr., and 
John M. Elliott. January 1958. 45p. diagrs., 
photos., tab. (NACA TN 4193. Supersedes 
RM L54D09) 



A FLIGHT INVESTIGATION OF THE EFFECTS OF 
VARIED LATERAL DAMPING ON THE EFFEC- 
TIVENESS OF A FIGHTER AIRPLANE AS A GUN 
PLATFORM. Helmut A. Kuehnel, Arnold R. 
Beckhardt. and Robert A. Champine. January 
1958. 30p. diagrs-, photo., tabs. (NACA TN 4199. 
Supersedes RM L53F08a) 



A METHOD FOR THE CALCULATION OF THE 
LATERAL RESPONSE OF AIRPLANES TO RANDOM 
TURBULENCE. John M. Eggleston and William H. 
Phillips. February 1958. 34p. diagrs., tab. 
(NACA TN 4196) 



A THEORETICAL ANALYSIS OF THE EFFECT OF 
ENGINE ANGULAR MOMENTUM ON LONGITUDINAL 
AND DIRECTIONAL STABmiTY IN STEADY ROLL- 
ING MANEUVERS. Ordway B. Gates, Jr., and 
C. H. Woodling. April 1958. 20p. diagrs., tab. 
(NACA TN 4249. Supersedes RM L55G05) 



WIND-TUNNEL INVESTIGATION AT LOW SPEEDS 
OF FLIGHT CHARACTERISTICS OF A SWEPTBACK- 
WING JET-TRANSPORT AIRPLANE MODEL 
EQUIPPED WITH AN EXTERNAL-FLOW JET- 
AUGMENTED SLOTTED FLAP. Joseph L. Johnson, 
Jr. July 1958. 32p. diagrs., photos., tab., film 
suppl. available on request. (NACA TN 4255) 



LOW-SPEED EXPERIMENTAL DETERMINATION OF 
THE EFFECTS OF LEADING-EDGE RADIUS AND 
PROFILE THICKNESS ON STATIC AND OSCILLA- 
TORY LATERAL STABILITY DERIVATr/ES FOR A 
DELTA WING WITH 60<> OF LEADING-EDGE SWEEP. 
Hermans. Fletcher. July 1958. 45p. diagrs., 
photos., tabs. (NACA TN 4341) 



MEASUREMENTS OF THE MOTIONS OF A LARGE 
SWEPT -WING AIRPLANE IN ROUGH AIR. Richard 
H. Rhyne. September 1958. 22p. diagrs., photo., 
tabs. (NACA TN 4310) 



APPROXIMATE METHOD FOR CALCULATING 
MOTIONS IN ANGLES OF ATTACK AND SIDESLIP 
DUE TO STEP PITCHING- AND YAWING-MOMENT 
INPUTS DURING STEADY ROLL. Martin T. Moul 
and Teresa R. Brennan. September 1958. 42p, 
diagrs., tabs. (NACA TN 4346) 



EFFECTS OF FREQUENCY AND AMPLITUDE ON 
THE YAWING DERIVATIVES OF TRIANGULAR, 
SWEPT, AND UNSWEPT WINGS AND OF A 
TRIANGULAR -WING- FUSELAGE COMBINATION 
WITH /..ID WITHOUT A TRIANGULAR TAIL PER- 
FORMING SINUSOIDAL YAWING OSCILLATIONS. 
William Letko and Herman S. Fletcher. September 
1958. 52p. diagrs., photos., tabs. (NACA TN 4390) 



(1.8.1.2.3) 

Damping Derivatives 



PRELIMINARY RESULTS OF THE FLIGHT INVES- 
TIGATION BETWEEN MACH NUMBERS OF 0.80 AND 
1.36 OF A ROCKET -POWERED MODEL OF A 
SUPERSONIC AIRPLANE CONFIGURATION HAVING 
A TAPERED WING WITH CIRCULAR-ARC SECTIONS 
AND 40° SWEEPBACK. Charles T. D'Aiutolo and 
Homer P. Mason. October 31, 1950. 30p. diagrs., 
photos., tab. (NACA RM L50H29a) 



DETERMINATION OF LONGITUDINAL STABILITY 
OF THE BELL X-l AIRPLANE FROM TRANSIENT 
RESPONSES AT MACH NUMBERS UP TO 1.12 AT 
LIFT COEFFICIENTS OF 0.3 AND 0.6. Ellwyn E. 
Angle and Euclid C. Holleman. November 7, 1950. 
22p diagrs. (NACA RM L 50106a) 



AN INVESTIGATION OF THE LONGITUDINAL 
CHARACTERISTICS OF THE X-3 CONFIGURATION 
USING ROCKET -PROPELLED MODELS. PRELIMI- 
NARY RESULTS AT MACH NUMBERS FROM 0.65 
TO 1.25. Jesse L. Mitchell and Robert F. Peck. 
December 1, 1950. 3 Op. diagrs., photos. 
(NACA RM L50J03) 



WING-ON AND WING-OFF LONGITUDINAL CHAR- 
ACTERISTICS OF AN AIRPLANE CONFIGURATION 
HAVING A THIN UNSWEPT TAPERED WING OF 
ASPECT RATIO 3, AS OBTAINED FROM ROCKET- 
PROPELLED MODELS AT MACH NUMBERS FROM 
0.8 TO 1.4. Clarence L. Gillis and A. James Vitale. 
March 14, 1951. 52p. diagrs., photos., tabs. 
(NACA RM L50K16) 



AN INVESTIGATION OF THE LONGITUDINAL CHAR- 
ACTERISTICS OF THE X-3 CONFIGURATION WITH 
WING AND HORIZONTAL TAIL SURFACES OF 
ASPECT RATIO 3.0 BY MEANS OF ROCKET- ' 
PROPELLED MODELS. RESULTS AT HIGH LIFT 
COEFFICIENTS. Robert F. Peck and Jesse L. 
Mitchell. August 27, 1951. 34p. diagrs., photos. 
(NACA RM L51G10) 



THE STATIC AND DYNAMIC LONGITUDINAL STA- 
BILITY CHARACTERISTICS OF SOME SUPERSONIC 
AIRCRAFT CONFIGURATIONS. Jesse L. Mitchell. 
January 1952. 19p. diagrs. (NACA RM L52A10a) 



158 



( 1 ) AERODYNAMICS 



LONGITUDINAL STABILITY AND DRAG CHARAC- 
TERISTICS AT MACH NUMBERS FROM 0.75 TO 1.5 
OF AN AIRPLANE CONFIGURATION HAVING A 60° 
SWEPT WING OF ASPECT RATIO 2.24 AS OB- 
TAINED FROM ROCKET-PROPELLED MODELS. 
A. James Vitale, John C. McFall, Jr., and John D. 
Morrow. April 1952. 43p. diagrs., photos'., tabs. 
(NACA RM L51K061 



LONGITUDINAL AERODYNAMIC CHARACTERISTICS 
OF MODEL AIRPLANE CONFIGURATION EQUIPPED 
WITH A SCALED X-l AIRPLANE WING . James H . 
Parks. April 1952. 37p. diagrs. 
(NACA RM LSlLlOa) 



EXPERIMENTAL INVESTIGATION OF THE STATIC 
AERODYNAMIC AND DYNAMIC DAM PING- IN -ROLL 
CHARACTERISTICS OF AN 8-CM AIRCRAFT 
ROCKET WITH SOLID AND SLOTTED FINS. Robert 
S. Chubb. June 1952. ii, 43p. diagrs., photo. 
(NACA RM A52C04) 



PRELIMINARY INVESTIGATION OF THE LOW- 
AMPLITUDE DAMPING IN PITCH OF TAILLESS 
DELTA- AND SWEPT -WING CONFIGURATIONS AT 
MACH NUMBERS FROM 0.7 TO 1.35. Charles T. 
D'Aiutolo and Robert N. Parker. August 1952. 27p. 
diagrs.. photos., tab. (NACA RM L52G09) 



LONGITUDINAL STABILITY, CONTROL EFFEC- 
TIVENESS, AND DRAG CHARACTERISTICS AT 
TRANSONIC SPEEDS OF A ROCKET -PROPELLED 
MODEL OF AN AIRPLANE CONFIGURATION 
HAVING AN UNSWEPT TAPERED WING OF ASPECT 
RATIO 3.0 AND NACA 65A004.5 AIRFOIL SECTIONS. 
JohnC. McFall, Jr., and James A. Hollinger: 
January 1953. 30p. diagrs., photos. 
(NACA RM L52L04) 



DAMPING IN PITCH OF LOW-ASPECT -RATIO 
WINGS AT SUBSONIC AND SUPERSONIC SPEEDS. 
Murray Tobak. April 1953. ii, 107p. diagrs. 
(NACA RM A52L04a) 



AN EXPERIMENTAL INVESTIGATION AT SUBSONIC 
AND SUPERSONIC SPEEDS OF THE TORSIONAL 
DAMPING CHARACTERISTICS OF A CONSTANT- 
CHORD CONTROL SURFACE OF AN ASPECT RATIO 
2 TRIANGULAR WING. David E. Reese, Jr. July 
1953. 32p. diagrs., photos., tab. 
(NACA RM A53D27) 



A ROCKET-MODEL INVESTIGATION OF THE LON- 
GITUDINAL STABILITY, LIFT, AND DRAG CHAR- 
ACTERISTICS OF THE DOUGLAS X-3 CONFIGURA- 
TION WITH HORIZONTAL TAIL OF ASPECT RATIO 
4.33. Robert F. Peck and James A. Hollinger. 
August 1953. 33p. diagrs., photos. 
(NACA RM L53F19a) 



NOTES ON DAMPING IN ROLL AND LOAD DISTRI- 
BUTIONS IN ROLL AT HIGH ANGLES OF ATTACK 
AND HIGH SUBSONIC SPEED. Richard E. Kuhn. 
August 1953. 18p. diagrs., tab. 
(NACA RM L53G13a) 



THEORETICAL CALCULATIONS OF THE STABILI- 
TY DERIVATIVES AT SUPERSONIC SPEEDS FOR A 
HIGH-SPEED AIRPLANE CONFIGURATION. 
Kenneth Margolis and Percy J. Bobbitt. October 
1953. 59p. diagrs., tab, (NACA RM L53G17) 



INVESTIGATION AT MACH NUMBERS OF 1 .62. 1 .93. 
AND 2.41 OF THE EFFECT OF OSCILLATION 
AMPLITUDE ON THE DAMPING IN PITCH OF 
DELTA-WING-BODY COMBINATIONS- Arthur 
Henderson, Jr. October 1953. 28p. diagrs.. 
photos. (NACA RM L53H25) 



LONGITUDINAL STABILITY CHARACTERISTICS 
AT TRANSONIC SPEEDS OF A ROCKET- 
PROPELLED MODEL OF AN AIRPLANE CON- 
FIGURATION HAVING A 450 SWEPT WING OF 
ASPECT RATIO 6.0. John C. McFall, Jr. 
January 1954. 34 p. diagrs., photos. 
(NACA RM L53G22a) 



AERODYNAMIC CHARACTERISTICS AT TRANSONIC 
AND SUPERSONIC SPEEDS OF A ROCKET- 
PROPELLED AIRPLANE CONFIGURATION HAVING 
A 52. 50 DELTA WING AND A LOW, SWEPT HORI- 
ZONTAL TAIL. Alan B. Kehlet. March 1954. 31p. 
diagrs., photos. (NACA RM L54A20) 



LOW-AMPLITUDE DAMPING -IN -PITCH CHARAC- 
TERISTICS OF TAILLESS DELTA -WING-BODY 
COMBINATIONS AT MACH NUMBERS FROM 0.80 
TO 1.35 AS OBTAINED WITH ROCKET-POWERED 
MODELS. Charles T. D'Aiutolo. June 1954. 34p. 
diagrs., photos., tab. (NACA RM L54D29) 



LOW-SPEED MEASUREMENT OF STATIC STABIL- 
ITY AND DAMPING DERIVATIVES OF A 60° 
DELTA-WING MODEL FOR ANGLES OF ATTACK 
OF 0O TO 90°. Donald E. Hewes. September 1954. 
30p. diagrs., photo., tab. (NACA RM L54G22a) 



AERODYNAMIC CHARACTERISTICS AT TRANSONIC 
AND SUPERSONIC SPEEDS OF A ROCKET- 
PROPELLED AIRPLANE CONFIGURATION HAVING 
A DIAMOND-PLAN-FORM WING OF ASPECT RATIO 
3.08 AND A LOW, SWEPT HORIZONTAL TAIL. 
Alan B. Kehlet. September 1954. 37p. diagrs., 
photos. (NACA RM L54G27a) 



LONGITUDINAL STABILITY CHARACTERISTICS AT 
TRANSONIC SPEEDS OF A CANARD CONFIGURA- 
TION HAVING A 45° SWEPTBACK WING OF ASPECT 
RATIO 6.0 AND NACA 65A009 AIRFOIL SECTION. 
A. James Vitale and John C. McFall, Jr. November 
1954. 24p. diagrs., photos., tab. 
(NACA RM L54IOU 



LOW-AMPLITUDE DAMPING-IN-PITCH CHARAC- 
TERISTICS OF FOUR TAILLESS SWEPT WING- 
BODY COMBINATIONS AT MACH NUMBERS FROM 
0.85 TO 1.30 AS OBTAINED WITH ROCKET- 
POWERED MODELS. Charles T. D'Aiutolo. 
November 1954. 34p. diagrs., photos., tab. 
(NACA RM L54I10) 



LOW -SPEED MEASUREMENTS OF ROLLING AND 
YAWING STABILITY DERIVATIVES OF A 60° 
DELTA-WING MODEL. Joseph L, Johnson, Jr. 
December 1954. 17p. diagrs,, tab. 
(NACA RM L54G27) 



ADDITIONAL MEASUREMENTS OF THE LOW- 
SPEED STATIC STABILITY OF A CONFIGURATION 
EMPLOYING THREE TRIANGULAR WING PANELS 
AND A BODY OF EQUAL LENGTH. Noel K. Delany. 
July 1955. 31p. diagrs. (NACA RM A55F02a) 



159 



(1) AERODYNAMICS 



FLIGHT MEASUREMENTS OF THE LATERAL 
RESPONSE CHARACTERISTICS OF THE CONVAIR 
XF-92A DELTA-WING AIRPLANE. Euclid C. 
Holleman. August 1955. 37p. diagrs., tabs. 
(NACA RM H55E26) 



AERODYNAMIC CHARACTERISTICS AT MACH NUM- 
BERS FROM 0.7 TO 1.75 OF A FOUR-ENGINE 
SWEPT-WING AIRPLANE CONFIGURATION AS 
OBTAINED FROM A ROCKET-PROPELLED MODEL 
TEST. Rowe Chapman, Jr. September 1955. 39p. 
diagrs., photos., tabs. (NACA RM L55F23) 



FREE-FLIGHT INVESTIGATION TO OBTAIN DRAG- 
AT-LIFT AND STABILITY DATA FOR A 60° DELTA- 
WING-BODY CONFIGURATION OVER A MACH NUM- 
BER RANGE OF 1.3 TO 1.6. Clement J. Welsh. 
October 1955. 23p. diagrs., photo., tab. 
(NACA RM L55G14) 



WIND-TUNNEL INVESTIGATION AT TRANSONIC 
SPEEDS OF A JET CONTROL ON AN 80° DELTA- 
WING MISSILE. Thomas R. Turner and Raymond D. 
Vogler. November 1955. 32p. diagrs. 
(NACA RM L55H22) 



EXPERIMENTAL INVESTIGATION AT HIGH SUB- 
SONIC SPEED OF THE ROLLING STABILITY 
DERIVATIVES OF A COMPLETE MODEL HAVING 
A CLIPPED-DELTA WING AND A HIGH HORIZON- 
TAL TAIL, William C. Sleeman, Jr., and Albert G. 
Few, Jr. February 1956. 32p. diagrs., tab. 
(NACA RM L55K11) 



LONGITUDINAL STABILITY INVESTIGATION FOR 
A MACH NUMBER RANGE OF 0.8 TO 1.7 OF AN 
AIRPLANE CONFIGURATION WITH A 45<> SWEPT 
WING AND A LOW HORIZONTAL TAIL. John C. 
McFail, Jr. February 1956. 32p. diagrs., photos., 
tab. (NACA RM L55L09) 



AN ANALOG STUDY OF THE RELATIVE IMPOR- 
TANCE OF VARIOUS FACTORS AFFECTING ROLL 
COUPLING . Joseph Weil and Richard E . Day . 
April 1956. 81p. diagrs., photo., tabs. 
(NACA RM H56A06) 



LOW -SPEED MEASUREMENTS OF STATIC STABIL- 
ITY, DAMPING IN YAW, AND DAMPING IN ROLL 
OF A DELTA, A SWEPT, AND AN UNSWEPT WING 
FOR ANGLES OF ATTACK FROM 0° TO 90°. 
Joseph L. Johnson, Jr. April 1956. 19p. diagrs., 
tabs . (NACA RM L 56B01) 



AERODYNAMIC DAMPING AT MACH NUMBERS OF 
1.3 AND 1.6 OF A CONTROL SURFACE ON A TWO- 
DIMENSIONAL WING BY THE FREE -OSCILLATION 
METHOD. W. J. Tuovila and Robert W. Hess. 
May 1956. 21p. diagrs., tabs. (NACA RM L56A26a) 



EFFECT OF WING HEIGHT AND DIHEDRAL ON THE 
LATERAL STABILITY CHARACTERISTICS AT LOW 
LIFT OF A 45° SWEPT-WING AIRPLANE CONFIG- 
URATION AS OBTAINED FROM TIME-VECTOR 
ANALYSES OF ROCKET-PROPELLED-MODEL 
FLIGHTS AT MACH NUMBERS FROM 0.7 TO 1.3. 
Clarence L. Gillis and Rowe Chapman, Jr. 
September 1956. 70p. diagrs., photos., tabs. 
(NACA RM L56E17) 



WIND-TUNNEL INVESTIGATION OF THE DAMPING 
IN ROLL OF THE DOUGLAS D-558-H RESEARCH 
AIRPLANE AND ITS COMPONENTS AT SUPERSONIC 
SPEEDS. Russell W. McDearmon. September 1356. 
36p. diagrs., photos. (NACA RM L56F07) 



WIND-TUNNEL INVESTIGATION OF DAMPING IN 
ROLL AT SUPERSONIC SPEEDS OF TRIANGULAR 
WINGS AT ANGLES OF ATTACK. Russell W. 
McDearmon and Robert A. Jones. September 1956. 
32p. diagrs., photos., tab. (NA<"A RM L56F13a) 



EXPERIMENTAL HINGE MOMENTS ON FREELY 
OSCILLATING FLAP-TYPE CONTROL SURFACES. 
C. William Martz. October 1956. 29p. diagrs., 
photos., tab. (NACA RM L56G20) 



LOW -SPEED MEASUREMENT OF TAIL CONTRI- 
BUTION TO ROLLING STABILITY DERIVATIVES 
AND AIR-FLOW ANGULARITY AT THE TAIL FOR 
AN X-TAIL MODEL IN STEADY ROLL INCLUDING 
SOME EFFECTS OF WING-TIP STORES. Donald R. 
Riley. November 1956. 28p. diagrs., photo., tab. 
(NACA RM L56I21) 



LINEARIZED LIFTING-SURFACE AND LIFTING- 
LINE EVALUATIONS OF SIDEWASH BEHIND ROLL- 
ING TRIANGULAR WINGS AT SUPERSONIC SPEEDS. 
Percy J. Bobbin. 1957. 11, 19p. diagrs., photo. 
(NACARept. 1301. Supersedes TN 3609) 



DETERMINATION OF LONGITUDINAL STABILITY 
AND CONTROL CHARACTERISTICS FROM FREE- 
FLIGHT MODEL TESTS WITH RESULTS AT TRAN- 
SONIC SPEEDS FOR THREE AIRPLANE CONFIGU- 
RATIONS. Clarence L. GiUis and Jesse L. Mitchell. 
1957. 11, 28p. diagrs., photos., tabs. 
(NACARept. 133Tk 



EXPERIMENTAL DETERMINATION AT SUBSONIC 
SPEEDS OF THE OSCILLATORY AND STATIC 
LATERAL STABILITY DERIVATIVES OF A SERIES 
OF DELTA WINGS WITH LEADING-EDGE SWEEP 
FROM 300 TO 86.50. William Letko. April 1957. 
38p. diagrs., photos., tab. (NACARM L57A30) 



A METHOD UTILIZING DATA ON THE SPIRAL, 
ROLL -SUBSIDENCE , AND DUTCH ROLL MODES 
FOR DETERMINING LATERAL STABILITY DERIV- 
ATIVES FROM FLIGHT MEASUREMENTS. Bernard 
B. Klawans and Jack A. White. August 1957. 38p. 
diagrs., tabs. (NACA TN 4066) 



EFFECT OF FREQUENCY OF SIDESLIPPING 
MOTION ON THE LATERAL STABILITY DERIVA- 
TIVES OF A TYPICAL DELTA-WING AIRPLANE. 
Jacob H. Ltchtenstein and James L. Williams. 
September 1957. 46p. diagrs., photos., tabs. 
(NACA RM L57F07) 



WIND-TUNNEL INVESTIGATION OF EFFECTS OF 
GROUND PROXIMITY AND OF SPLIT FLAPS ON 
THE LATERAL STABILITY DERIVATIVES OF A 60<> 
DELTA-WING MODEL OSCILLATING IN YAW. 
Byron M. Jaquet. September 1957. 32p. diagrs. 
photos., tab. (NACA TN 4119) 



160 



(1) AERODYNAMICS 



ON THE MINIMIZATION OF AIRPLANE RESPONSES 
TO RANDOM GUSTS . Murray Tobak. October 
1957. 71p. diagrs. (NAGA TN 3290) 



FLIGHT INVESTIGATION OF THE TRANSONIC 
LONGITUDINAL AND LATERAL HANDLING QUAL- 
ITIES OF THE DOUGLAS X-3 RESEARCH AIRPLANE. 
Jack Fischel, Euclid C. Holleman, and Robert A. 
Tremant. December 1957. 61p. diagrs., photos., 
tab. (NACA RM H57I05) 



EFFECT OF ANGLE OF ATTACK AND THICKNESS 
ON AERODYNAMIC COEFFICIENTS OF A RIGID 
WING OSCILLATING AT VERY LOW FREQUENCIES 
IN TWO-DIMENSIONAL SUPERSONIC FLOW. 
Frank S. Malvestuto, Jr., and Julia M. Goodwin. 
January 1958. 65p. diagrs. (NACA TN 4069) 



WIND-TUNNEL INVESTIGATION OF EFFECT OF 
SWEEP-ON ROLLING DERIVATIVES AT ANGLES OF 
ATTACK UP TO 13° AND AT HIGH SCBSONIC MACH 
NUMBERS, INCLUDING A SEMIEMPIRICAL 
METHOD OF ESTIMATING THE ROLLING DERIVA- 
TIVES. James W. Wiggins. January 1958. 47p. 
diagrs., tab. (NACA TN 4185. Supersedes * 
RM L54C26) 



LIFT AND MOMENT ON THIN ARROWHEAD WINGS 
WITH SUPERSONIC EDGES OSCILLATING IN 
SYMMETRIC FLAPPING AND ROLL AND APPLI- 
CATION TO THE FLUTTER OF AN ALL-MOVABLE 
CONTROL SURFACE. H. J. Cunningham. January 
1958. 58p. diagrs. (NACA TN 4189) 



SOME MEASUREMENTS OF AERODYNAMIC 
FORCES AND MOMENTS AT SUBSONIC SPEEDS 
ON A RECTANGULAR WING OF ASPECT RATIO 2 
OSCILLATING ABOUT THE MIDCHORD. Edward 
Widmayer, Jr., Sherman A. Clevenson, and 
Sumner A. Leadbetter. May 1958. 45p. diagrs., 
tabs. (NACA TN 4240. Supersedes RM L53F19) 



LOW-SPEED EXPERIMENTAL DETERMINATION OF 
THE EFFECTS OF LEADING-EDGE RADIUS AND 
PROFILE THICKNESS ON STATIC AND OSCILLA- 
TORY LATERAL STABILITY DERT/ATIVES FOR A 
DELTA WING WITH 60<> OF LEADING-EDGE SWEEP. 
Hermans. Fletcher. July 1958. 45p. diagrs,, 
photos., tabs. (NACA TN 4341) 



ANALYTICAL AND EXPERIMENTAL INVESTIGA- 
TION OF AERODYNAMIC FORCES AND MOMENTS 
ON LOW-ASPECT-RATIO WINGS UNDERGOING 
FLAPPING OSCILLATIONS. Donald S. Woolston, 
Sherman A. Clevenson, and Sumner A. Leadbetter. 
August 1958. 25p. diagrs., tab. (NACA TN 4302) 



EFFECTS OF FREQUENCY AND AMPLITUDE ON 
THE YAWING DERIVATIVES OF TRIANGULAR, 
SWEPT, AND UNSWEPT WINGS AND OF A 
TRIANGULAR-JWING-FUSELAGE COMBINATION 
WITH AND WITHOUT A TRIANGULAR TAIL PER- 
FORMING SINUSOIDAL YAWING OSCILLATIONS. 
William Letko and Herman S. Fletcher. September 
1958. 52p. diagrs., photos., tabs. (NACA TN 4390) 



(1.8.2) 
CONTROL 



LOW-SPEED MEASUREMENT OF STATIC STABIL- 
ITY AND DAMPING DERT/ATIVES OF A 60° 
DELTA-WING MODEL FOR ANGLES OF ATTACK 
OF 0° TO 90°. Donald E. Hewes. September 1954. 
30p. diagrs., photo., tab. (NACA RM L54G22a) 



AN ANALOG COMPUTER STUDY OF SEVERAL STA- 
BILITY AUGMENTATION SCHEMES DESIGNED TO 
ALLEVIATE ROLL-INDUCED INSTABDHTY. Brent 
Y. Creer. February 1957. 50p. diagrs., tab. 
(NACA RM A56H30) 



SOME GROUND MEASUREMENTS OF THE FORCES 
APPLIED BY PILOTS TO A SIDE -LOCATED AIR- 
CRAFT CONTROLLER. Roy F. Brissenden. 
November 1957. 17p. diagrs., photos., tab. 
(NACA TN 4171) 



FLIGHT INVESTIGATION OF THE ACCEPTABILITY 
OF A SMALL SIDE -LOCATED CONTROLLER USED 
WITH AN IRREVERSIBLE HYDRAULIC CONTROL 
SYSTEM. Helmut A. Kuehnel and Robert W. Sommer. 
July 1958. 19p. diagrs., photos., tabs. 
(NACA TN 4297) 



(1.8.2. 1) 

LONGITUDINAL 



FLIGHT TESTS AT TRANSONIC AND SUPERSONIC 
SPEEDS OF AN AIRPLANE-LIKE CONFIGURATION 
WITH THIN STRAIGHT SHARP -EDGE WINGS AND 
TAIL SURFACES. Clarence L. Gillis and Jesse L. 
Mitchell. January 5, 1949. 37p. diagrs., photos., 
tab. (NACA RM L8K04a) 



ESTIMATED TRANSONIC FLYING QUALITIES OF A 
TAILLESS AIRPLANE BASED ON A MODEL INVES- 
TIGATION. Charles J . Donlan and Richard E . Kuhn. 
June 8, 1949. 63p. diagrs., photos., tabs'. 
(NACA RM L9D08) 



AERODYNAMIC STUDY OF A WING-FUSELAGE 
COMBINATION EMPLOYTNG A WING SWEPT BACK 
63°. - EFFECTS AT SUBSONIC SPEEDS OF A 
CONSTANT-CHORD ELEVON ON A WING CAM- 
BERED AND TWISTED FOR A UNIFORM LOAD AT 
A LIFT COEFFICIENT OF 0.25. J. Lloyd Jones and 
Fred A. Demele. December 5, 1949. 44p. diagrs., 
photos., tab. (NACA RM A9I27) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR-ARC SECTIONS AND 40° SWEEPBACK. 
STATIC LONGITUDINAL STABILITY AND CONTROL 
CHARACTERISTICS AT A MACH NUMBER OF 1.40. 
M. Leroy Spearman. April 3, 1950. 27p. diagrs., 
photos., tab. (NACA RM L9L08) 



WIND-TUNNEL TESTS OF A 0.16-SCALE MODEL 
OF THE X-3 AIRPLANE AT HIGH SUBSONIC 
SPEEDS. STABILITY AND CONTROL CHARACTER- 
ISTICS. William T. Hamilton and Joseph W . Cleary. 
April 21, 1950. 129p. diagrs., photos., tabs. 
(NACA RM A50A03) 



161 



(1) AERODYNAMICS 



WIND-TUNNEL TESTS OF A 0.16-SCALE MODEL 
OF. THE X-3 AIRPLANE, AT HIGH SUBSONIC SPEEDS. 
- ADDITIONAL STABILITY AND CONTROL CHAR- 
ACTERISTICS AND THE AERODYNAMIC EFFECTS 
OF EXTERNAL STORES AND RAM JETS . Joseph W. 
Cleary and Jack A. Mellenthin. June 13, 1950. 86p. 
diagrs., photos., tabs. (NACA RM A50C30) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR -ARC SECTIONS AND 40° SWEEPBACK. 
STATIC LONGITUDINAL STABILITY AND CONTROL 
CHARACTERISTICS AT A MACH NUMBER OF 1.59. 
M, Leroy Spearman and John H. Hilton, Jr. 
June 29, 1950. 22p. diagrs., photo., tab. 
(NACA RM L50E12) 



DETERMINATION OF LONGITUDINAL STABILITY 
OF THE BELL X-l AIRPLANE FROM TRANSIENT 
RESPONSES AT MACH NUMBERS UP TO 1.12 AT 
LIFT COEFFICIENTS OF 0.3 AND 0.6. Ellwyn E. 
Angle and Euclid C. Holleman. November 7, 1950. 
22p diagrs. (NACA RM L50I06a) 



AN INVESTIGATION OF THE LONGITUDINAL 
CHARACTERISTICS OF THE X-3 CONFIGURATION 
USING ROCKET-PROPELLED MODELS. PRELIMI- 
NARY RESULTS AT MACH NUMBERS FROM 0.65 
TO 1.25. Jesse L. Mitchell and Robert F. Peck. 
December 1, 1950. 3 Op. diagrs., photos. 
(NACA RM L50J03) 



WING -ON AND WING-OFF LONGITUDINAL CHAR- 
ACTERISTICS OF AN AIRPLANE CONFIGURATION 
HAVING A THIN UNSWEPT TAPERED WING OF 
ASPECT RATIO 3, AS OBTAINED FROM ROCKET- 
PROPELLED MODELS AT MACH NUMBERS FROM 
0.8 TO 1 4. Clarence L. Gillis and A . James Vitale. 
March 14, 1951. 52p. diagrs., photos., tabs. 
(NACA RM L50K16) 



AN INVESTIGATION OF THE LONGITUDINAL CHAR- 
ACTERISTICS OF THE X-3 CONFIGURATION WITH 
WING AND HORIZONTAL TAIL SURFACES OF 
ASPECT RATIO 3.0 BY MEANS OF ROCKET- 
PROPELLED MODELS. RESULTS AT HIGH LIFT 
COEFFICIENTS. Robert F. Peck and Jesse L. 
Mitchell. August 27, 1951. 34p. diagrs., photos. 
4NACA RM L51G10) 



ANALYSIS OF LONGITUDINAL STABILITY AND 
TRIM OF THE BELL X-l AIRPLANE AT A LIFT 
COEFFICIENT OF 0.3 TO MACH NUMBERS NEAR 
1.05. Hubert M. Drake, John R. Carden, and 
Harry P. Clagett. October 1951. 30p. diagrs., 
photo., tab. (NACA RM L51H01) 



FLIGHT DETERMINATION OF THE DRAG AND 
LONGITUDINAL STABrLTTY AND CONTROL CHAR- 
ACTERISTICS OF A ROCKET -POWERED MODEL 
OF A 60° DELTA-WING AIRPLANE FROM MACH 
NUMBERS OF 0.75 TO 1.70. Grady L. Mitcham, 
Norman L. CrabiU, and Joseph E. Stevens. 
November 1951. 44p. diagrs., photos., tab. 
(NACA RM L51I04) 



THE STATIC AND DYNAMIC LONGITUDINAL STA- 
BILITY CHARACTERISTICS OF SOME SUPERSONIC 
AIRCRAFT CONFIGURATIONS. Jesse L. Mitchell. 
January 1952. 19p. diagrs. (NACA RM L52A10a) 



LONGITUDINAL STABILITY AND DRAG CHARAC- 
TERISTICS AT MACH NUMBERS FROM 0.75 TO 1.5 
OF AN AIRPLANE CONFIGURATION HAVING A 60° 
SWEPT WING OF ASPECT RATIO 2.24 AS OB- 
TAINED FROM ROCKET-PROPELLED MODELS. 
A. James Vitale, John C. McFall, Jr., and John D. 
Morrow. April 1952. 43p. diagrs., photos., tabs. 
(NACA RM L51K06) 



LONGITUDINAL AERODYNAMIC CHARACTERISTICS 
OF MODEL AIRPLANE CONFIGURATION EQUIPPED 
WITH A SCALED X-l AIRPLANE WING. James H. 
Parks. April 1952. 37p. diagrs. 
(NACA RM L51L10a) 



THE AERODYNAMIC CHARACTERISTICS OF A 
SUPERSONIC AIRCRAFT CONFIGURATION WITH A 
40° SWEPTBACK WING THROUGH A MACH NUM- 
BER RANGE FROM TO 2.4 AS OBTAINED FROM 
VARIOUS SOURCES. M. Leroy Spearman and Ross 
B. Robinson. April 1952. 50p. diagrs., photo., 
tab. (NACA RM L52A21) 



AN INVESTIGATION OF A 0.16-SCALE MODEL OF 
THE DOUGLAS X-3 AIRPLANE. TO DETERMINE 
MEANS OF IMPROVING THE LOW -SPEED LONGI- 
TUDINAL STABILITY AND CONTROL CHARACTER- 
ISTICS. JohnW. McKee and John M. Riebe. 
November 1952. 90p. diagrs., photos., tabs. 
(NACA RML52H01) 



AN ANALYSIS OF THE EFFECT OF A CURVED 
RAMP ON THE TAKE-OFF PERFORMANCE OF 
CATAPULT-LAUNCHED AIRPLANES. Wilmer H. 
Reed, in. November 1952. 28p. diagrs., tab. 
(NACA RM L 5 21 05) 



TOTAL-PRESSURE AND SCHUEREN STUDDZS OF 
THE WAKES OF VARIOUS CANARD CONTROL SUR- 
FACES MOUNTED ON A MISSILE BODY AT A MACH 
NUMBER OF 1.93. William B. Bo at right. 
November 1952. 47p. photos., diagrs. 
(NACA RM L 5 2129) 



HINGE-MOMENT CHARACTERISTICS FOR SEVER- 
AL TIP CONTROLS ON A 60° SWEPTBACK DELTA 
WING AT MACH NUMBER 1.61. K. R. Czarneckl 
and Douglas R. Lord. January 1953. 31p. diagrs., 
photos. (NACA RM L52K28) 



LONGITUDINAL STABILITY, CONTROL EFFEC- 
TIVENESS, AND DRAG CHARACTERISTICS AT 
TRANSONIC SPEEDS OF A ROCKET -PROPELLED 
MODEL OF AN AIRPLANE CONFIGURATION 
HAVING AN UNSWEPT TAPERED WING OF ASPECT 
RATIO 3.0 AND NACA 65A0O4.5 AIRFOIL SECTIONS. 
JohnC. McFall, Jr., and James A. Hollinger. 
January 1953. 30p. diagrs., photos. 
(NACA RM L52L04) 



SOME MEASUREMENTS OF FLYING QUALITIES OF 
A DOUGLAS D-558-n RESEARCH AIRPLANE DUR- 
ING FLIGHTS TO SUPERSONIC SPEEDS. Herman O. 
Ankenbruck and Theodore E. Dahlen. March 1953. 
25p. diagrs., photos., tab. (NACA RM L53A06) 



162 



(1) AERODYNAMICS 



A THEORETICAL STUDY OF THE EFFECT OF 
CONTROL-DEFLECTION AND CONTROL-RATE 
LIMITATIONS ON THE NORMAL ACCELERATION 
AND ROLL RESPONSE OF A SUPERSONIC INTER- 
C EPTOR . Howard F . Matthews and Stanley F . 
Schmidt. April 1953. 28p. photos., diagrs., 
tabs. (NACA RM A53B11) 



LOADS DUE TQ FLAPS AND SPOILERS ON SWEPT - 
BACK WINGS AT SUPERSONIC AND TRANSONIC 
SPEEDS. Alexander D. Hammond and F. E. West, 
Jr. June 1953. 17p. diagrs. (NACA RM L53D29a) 



A STUDY OF VISUAL INTERCEPTION ATTACKS 
ON A NONMANEUVERING AIRPLANE TARGET. 
Donald C. Cheatham, Charles W. Mathews, and 
John A. Harper. July 1953. 97p. diagrs., photos., 
tabs. (NACA RM L53E01) 



A FLIGHT INVESTIGATION AT MACH NUMBERS 
FROM 0.67 TO 1.81 OF THE LONGITUDINAL 
STABILITY AND CONTROL CHARACTERISTICS OF 
A 60<> DELTA-WING MISSILE CONFIGURATION 
HAVING AN ALL-MOVABLE TAIL. Martin T. 
Moul and Hal T. Baber, Jr. October 1953. 43p. 
diagrs., photo. (NACA RM L53G29) 



SUBSONIC AND SUPERSONIC HINGE-MOMENT AND 
EFFECTIVENESS CHARACTERISTICS OF AN UN- 
BALANCED LATERAL CONTROL HAVING LOW 
THEORETICAL HINGE MOMENTS AT SUPERSONIC 
SPEEDS. Kennith L. Goln and William E. Palmer. 
October 1953. 55p. diagrs., photos. 
(NACA RM L53G31a) 



THE INTERPRETATION OF NONLINEAR PITCHING 
MOMENTS IN RELATION TO THE PITCH -UP 
PROBLEM. George S. Campbell and Joseph Weil. 
October 1953. 32p. diagrs., tabs. 
(NACA RM L53I02) 



ROCKET -MODEL INVESTIGATION TO DETERMINE 
THE HINGE-MOMENT AND NORMAL-FORCE 
PROPERTIES OF A FULL-SPAN, CONSTANT- 
CHORD, PARTIALLY BALANCED TRAILING-EDGE 
CONTROL ON A 60° CLIPPED DELTA WING BE- 
TWEEN MACH NUMBERS OF 0.50 AND 1.26. 
C. William Martz and John W. Goslee. October 
1953. 33p. diagrs., photos., tab. 
(NACA RM L53I04) 



FLIGHT MEASUREMENTS OF THE HORIZONTAL- 
TAIL LOADS ON A SWEPT-WING FIGHTER AIR- 
PLANE AT TRANSONIC SPEEDS. Melvin Sadoff. 
November 1953. 58p. diagrs., photo., tab. 
(NACA RM A53G10) 



LOW-SPEED STATIC STABILITY AND CONTROL 
CHARACTERISTICS OF A 1/4-SCALE MODEL OF 
THE BELL X-l AIRPLANE EQUIPPED WITH A 
4-PERCENT -THICK, ASPECT-RATIO-4, UNSWEPT 
WING. William C. Moseley, Jr., and Robert T. 
Taylor. November 1953. 53p. diagrs., photos., 
tab. (NACA RM L53H27) 



STATIC LONGITUDINAL STABILITY AND CONTROL 
CHARACTERISTICS OF A 1/16-SCALE MODEL OF 
THE DOUGLAS D-558-II RESEARCH AIRPLANE AT 
MACH NUMBERS OF 1.61 AND 2.01. M. Leroy 
Spearman. November 1953. 34p. diagrs., tabs. 
(NACA RM L53I22) 



EFFECT OF LARGE DEFLECTIONS OF A CANARD 
CONTROL AND DEFLECTIONS OF A WING-TB? 
CONTROL ON THE STATIC -STABILITY AND 
INDUCED-ROLL CHARACTERISTICS OF A CRUCI- 
FORM CANARD MISSILE AT A MACH NUMBER OF 
2.01. M. Leroy Spearman. December 1953. 20p. 
diagrs., tabs. (NACA RM L53K03) 



INVESTIGATION OF A TRAILING-EDGE PADDLE- 
CONTROL SURFACE ON A TRIANGULAR WING OF 
ASPECT RATIO 2 AT SUBSONIC AND SUPERSONIC 
SPEEDS. Louis H. Ball. February 1954. 18p. 
diagrs., tab. (NACA RM A53K20) 



DETERMINATION OF LONGITUDINAL STABILITY 
IN SUPERSONIC ACCELERATED MANEUVERS FOR 
THE DOUGLAS D-558-H RESEARCH AIRPLANE. 
Herman O. Ankenbruck. February 1954. 29p. 
diagrs., photos., tab. (NACA RM L53J20) 



EFFECT OF WING SLATS AND INBOARD WING 
FENCES ON THE LONGITUDINAL STABILITY 
CHARACTERISTICS OF THE DOUGLAS D-558-H 
RESEARCH AIRPLANE IN ACCELERATED MANEU- 
VERS AT SUBSONIC AND TRANSONIC SPEEDS. 
Jack Fischel. February 1954. 125p. diagrs., 
photos., tabs. (NACA RM L53L16) 



AERODYNAMIC CHARACTERISTICS OF A FULL- 
SPAN TRAILING-EDGE CONTROL ON A 60° DELTA 
WING WITH AND WITHOUT A SPOILER AT MACH 
NUMBER 1.61. Douglas R. Lord and K. R. 
Czarnecki. March 1954. 49p. diagrs., photos., 
tab. (NACARML53L17) 



AERODYNAMIC CHARACTERISTICS AT TRANSONIC 
AND SUPERSONIC SPEEDS OF A ROCKET- 
PROPELLED AIRPLANE CONFIGURATION HAVING 
A 52. SO DELTA WING AND A LOW, SWEPT HORI- 
ZONTAL TAIL. Alan B. Kehlet. March 1954. 31p. 
diagrs., photos. (NACA RM L54A20) 



ROCKET -POWERED MODEL niVESTIGATION OF 
LIFT, DRAG, AND STABILITY OF A BODY -TAIL 
CONFIGURATION AT MACH NUMBERS FROM 0.8 
TO 2.3 AND ANGLES OF ATTACK BETWEEN ±6.5°. 
Warren Gillespie, Jr., and Albert E. Dietz. April 
1954. 42p. diagrs., photos., tabs. 
(NACA RM L54C04) 



A FLIGHT INVESTIGATION AT TRANSONIC SPEEDS 
OF THE AERODYNAMIC CHARACTERISTICS OF A 
MODEL HAVING A THIN UNSWEPT WING OF 
ASPECT RATIO 3.1. Maurice D. White. August 
1954. 41p. diagrs., photo., tabs. 
(NACA RM A54E12) 



PRELIMINARY WIND-TUNNEL INVESTIGATION OF 
TWO TYPES OF JET-EXIT CONFIGURATIONS FOR 
CONTROL OF AIRCRAFT. Gerald W. Englert and 
L- Abbott Leissler. August 1954. 20p. diagrs. 
(NACA RM E54E27) 



AERODYNAMIC CHARACTERISTICS OF SEVERAL 
TIP CONTROLS ON A 60° DELTA WING AT A MACH 
NUMBER OF 1.61. Douglas R. Lord and K. R. 
Czarnecki. August 1954. 44p. diagrs., photos., 
tabs. (NACA RM L54E25) 



163 



(1) AERODYNAMICS 



WIND-TUNNEL INVESTIGATION AT A MACH NUM- 
BER OF 2.01 OF THE AERODYNAMIC CHARACTER- 
ISTICS IN COMBINED PITCH AND SIDESLIP OF 
SOME CANARD-TYPE MISSILES HAVING CRUCI- 
FORM WINGS AND CANARD SURFACES WITH 70° 
DELTA PLAN FORMS. M. Leroy Spearman-and 
Cornelius Driver. August 1954. 121p. diagrs., 
tabs. (NACA RM L54F09) 



EFFECTS OF CANOPY, REVISED VERTICAL TAIL, 
AND A\YAW-DAMPER VANE ON THE AERODYNAM- 
IC CHARACTERISTICS OF A l/16-SCALE MODEL 
OF THE DOUGLAS D-558-H RESEARCH AIRPLANE 
AT A MACH NUMBER OF 2.01. Ross B. Robinson. 
August 1954. 29p. diagrs., tabs. 
(NACA RM L54F25) 



AERODYNAMIC CHARACTERISTICS AT TRANSONIC 
AND SUPERSONIC SPEEDS OF A ROCKET- 
PROPELLED AIRPLANE CONFIGURATION HAVING 
A DIAMOND-PLAN-FORM WING OF ASPECT RATIO 
3.08 AND A LOW, SWEPT HORIZONTAL TAIL. 
Alan B. Kehlet. September 1954. 37p. diagrs., 
photos. (NACA RM L54G27a) 



LONGITUDINAL STABILITY CHARACTERISTICS IN 
ACCELERATED MANEUVERS AT SUBSONIC AND 
TRANSONIC SPEEDS OF THE DOUGLAS D-558-II 
RESEARCH AIRPLANE EQUIPPED WITH A 
LEADING-EDGE WING CHORD-EXTENSION. Jack 
Fischel and Cyril D. Brunn. October 1954. 6 Up. 
diagrs., photos., ia.u. (NACA RM H54H1C) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR-ARC SECTIONS AND 40° SWEEPBACK. 
STATIC LONGITUDINAL AND LATERAL STABILITY 
AND CONTROL CHARACTERISTICS AT A MACH 
NUMBER OF 1.89. M. Leroy Spearman and Edward 
B. Palazzo. October 1954. 24p. diagrs., photo., 
tab. (NACA RM L54G26a) 



ANALYTICAL STUDY OF THE EFFECT OF 
CENTER-OF- GRAVITY POSITION ON THE RE- 
SPONSE TO LONGITUDINAL CONTROL IN LANDING 
APPROACHES OF A SWEPT -WING AIRPLANE OF 
LOW ASPECT RATIO HAVING NO HORIZONTAL 
TAIL. Ralph W. Stone, Jr. October 1954. 35p. 
diagrs., tabs. (NACA RM L54H04) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR -ARC SECTIONS AND 40° SWEEPBACK. 
AERODYNAMIC CHARACTERISTICS OF THE CON- 
FIGURATION EQUIPPED WITH A CANARD CON- 
TROL SURFACE AT A MACH NUMBER OF 1.89. 
M. Leroy Spearman and Edward B. Palazzo. 
October 1954. 22p. diagrs., photo., tab. 
(NACA RM L54H19) 



THE EFFECT OF AN OP*,«AilNG PROPELLER ON 
THE AERODYNAMIC CHARACTERISTICS AT HIGH 
SUBSONIC SPEEDS OF A MODEL OF A VERTICAL- 
RISING AIRPLANE HAVING AN UNSWEPT WING OF 
ASPECT RATIO 3. Fred B. Sutton and Donald A. 
BuelL. November 1954. 90p. diagrs., photos., 
tabs. (NACA RM A52E06) 



DETERMINATION OF LONGITUDINAL HANDLING 
QUALITIES OF THE D-558-U RESEARCH AIRPLANE 
AT TRANSONIC AND SUPERSONIC SPEEDS TO A 
MACH NUMBER OF ABOUT 2.0. Herman O. 
Ankenbruck. November 1954. 25p. diagrs., photos., 
tab. (NACA RM H54G29a) 



LONGITUDINAL STABILITY CHARACTERISTICS 
AT MACH NUMBERS UP TO 0.92 OF A WING- 
BODY-TAIL COMBINATION HAVING A WING WITH 
45° OF SWEEPBACK AND A TAIL IN VARIOUS 
VERTICAL POSITIONS. Jack D. Stephenson, 
Angelo Bandettini, and Ralph Selan. January 1955. 
64p. diagrs., photos., tabs. (NACA RM A54K09) 



THE LONGITUDINAL CHARACTERISTICS AT MACH 
NUMBERS UP TO 0.92 OF SEVERAL WING- 
FUSELAGE-TAIL COMBINATIONS HAVING SWEPT - 
BACK WINGS WITH NACA FOUR-DIGIT THICKNESS 
DISTRIBUTIONS. Fred B. Sutton and Jerald K. 
Dickson. March 1955. 128p. diagrs., photos., tab. 
(NACA RM A54L08) 



A THEORETICAL INVESTIGATION OF THE EF- 
FECT OF AUXILIARY DAMPING ON THE LONGI- 
TUDINAL RESPONSE OF A TRANSONIC BOMBER 
CONFIGURATION IN FLIGHT THROUGH CON- 
TINUOUS TURBULENCE. T. F. Bridgland, Jr. 
March 1955. 26p. diagrs., tab. 
(NACA RM L54K15a) 



EXPLORATORY INVESTIGATION OF THE LOW- 
SPEED STATIC STABILITY OF A CONFIGURATION 
EMPLOYING THREE IDENTICAL TRIANGULAR 
WING PANELS AND A BODY OF EQUAL LENGTH. 
NoelK. Delany. April 1955. 25p. diagrs., photos. 
(NACA RM A55C28) 



LIFT, DRAG, AND LONGITUDINAL STABILITY AT 
MACH NUMBERS FROM 0.8 TO 2.1 OF A ROCKET- 
POWERED MODEL HAVING A TAPERED UNSWEPT 
WING OF ASPECT RATIO 3 AND INLINE TAIL 
SURFACES. Warren Gillespie, Jr. April 1955. 
29p. diagrs., photo., tabs. (NACA RM L55B10) 



STABILITY AND CONTROL CHARACTERISf 1CS 
OBTAINED DURING DEMONSTRATION OF THE 
DOUGLAS X-3 RESEARCH AIRPLANE. Richard E. 
Day and Jack Fischel. July 1955. 51p. diagrs., 
photos., tab. (NACA RM H55E16) 



SIMULATOR STUDIES OF THE ATTACK PHASE OF 
AN AUTOMATICALLY CONTROLLED INTERCEP- 
TOR. I - PRELIMINARY STUDIES OF THE LATER- 
AL AND LONGITUDINAL CONTROL SYSTEMS. 
Albert A. Schy, Ordway B. Gates, Jr., and C. H. 
Woodling. II - SOME RESULTS OF A STUDY PER- 
FORMED ON THE TYPHOON COMPUTER. Windsor 
L. Sherman and Leonard Sternfield. August 1955. 
24p. diagrs. (NACA RM L55E27a) 



AERODYNAMIC CHARACTERISTICS AT MACH NUM- 
BERS FROM 0.7 TO 1.75 OF A FOUR-ENGINE 
SWEPT-WING AIRPLANE CONFIGURATION AS 
OBTAINED FROM A ROCKET-PROPELLED MODEL 
TEST. Rowe Chapman, Jr. September 1955. 39p. 
diagrs., photos., tabs. (NACA RM L55F23) 



A THEORETICAL ANALYSIS OF A SIMPLE AERO- 
DYNAMIC DEVICE TO IMPROVE THE LONGITUDI- 
NAL DAMPING OF A CRUCIFORM MISSILE CON- 
FIGURATION AT SUPERSONIC SPEEDS. James E. 
Clements. October 1955. 36p. diagrs., tab. 
(NACA RM L55H31) 



164 



( 1 ) AERODYNAMICS 



WIND-TUNNEL INVESTIGATION AT TRANSONIC 
SPEEDS OF A JET CONTROL ON AN 80° DELTA- 
WING MISSILE. Thomas R. Turner and Raymond D. 
Vogler. November 1955. 32p. diagrs. 
(NACA RM L55H221 



THE EFFECT OF LEADING-EDGE EXTENSIONS 
OF THE LONGITUDINAL CHARACTERISTICS AT 
MACH NUMBERS' UP TO 0.92 OF A WING- 
FUSELAGE-TAIL COMBINATION HAVING A 40° 
SWEPTBACK WING WITH NACA 64A THICKNESS 
DISTRIBUTION. Fred B. Sutton. January 1956. 
52p. diagrs., photos., tabs. (NACA RM A55I29) 



AN INVESTIGATION OF THE AERODYNAMIC CHAR- 
ACTERISTICS AT TRANSONIC MACH NUMBERS OF 
A SWEPT -WING SUPERSONIC BOMBER CONFIGU- 
RATION. Ralph P. Bielat and J. Lawrence Cooper. 
February 1956. 92p. diagrs., photos., tabs. 
(NACA RM L53F05) 



A TRANSONIC WIND-TUNNEL INVESTIGATION OF 
STORE AND HORIZONTAL-TAIL LOADS AND SOME 
EFFECTS OF FUSELAGE -AFTERBODY MODIFICA- 
TIONS ON A SWEPT -WING FIGHTER AIRPLANE^ 
Joseph M. Hallissy, Jr., and Louis Kudlacik. April 
1956. 79p. diagrs., photos. (NACA RM L56A26) 



AN EVALUATION OF AN AEROMECHANIC A L 
METHOD OF MINIMIZING SERVO-MISSILE 
TRANSFER-FUNCTION VARIATIONS WITH FLIGHT 
CONDITION. Martin L. Nason. April 1956. 41p. 
diagrs., tabs. (NACA RM L56A31) 



WIND-TUNNEL INVESTIGATDN OF A RAM-JET 
MISSILE MODEL HAVING A WING AND CANARD 
SURFACES OF DELTA PLAN FORM WITH 70° 
SWEPT LEADING EDGES. FORCE AND MOMENT 
CHARACTERISTICS AT COMBINED ANGLES OF 
PITCH AND SIDESLIP FOR MACH NUMBER 2.01. 
Cornelius Driver and Clyde V. Hamilton. April 
1956. 67p. diagrs., photo., tabs. 
(NACA RM L56B21) 



FULL-SCALE WIND-TUNNEL TESTS OF THE LON- 
GITUDINAL STABILITY AND CONTROL CHARAC- 
TERISTICS OF THE XV-1 CONVERTIPLANE IN THE 
AUTOROTATING FLIGHT RANGE. David H. Hickey. 
May 1956. 64p. diagrs., photos., tabs. 
(NACA RM A55K21a) 



A HORIZONTAL -TAIL ARRANGEMENT FOR 
COUNTERACTING STATIC LONGITUDINAL 
INSTABILITY OF SWEPTBACK WINGS. George G. 
Edwards and Howard F. Savage. May 1956. 51p. 
diagrs., photos., tab. (NACA RM A56D06) 



EFFECT OF WING CAMBER AND TWIST AT MACH 
NUMBERS FROM 1.4 TO 2.1 ON THE LIFT, DRAG, 
AND LONGITUDINAL STABILITY OF A ROCKET- 
POWERED MODEL HAVING A 52.5° SWEPTBACK 
WING OF ASPECT RATIO 3 AND INLINE TAIL SUR- 
FACES. Warren Gillespie, Jr. May 1956. 29p. 
diagrs., photos., tabs. (NACA RM L56C16) 



EFFECT OF SEVERAL WING MODIFICATIONS ON 
THE SUBSONIC AND TRANSONIC LONGITUDINAL 
HANDLING QUALITIES OF THE DOUGLAS D-558-II 
RESEARCH AIRPLANE. Jack Fischel and Donald 
Reisert. June 1956. 57p. diagrs., photos., tabs. 
(NACA RM H56C30) 



THE USE OF AREA SUCTION FOR THE PURPOSE 
OF IMPROVING THE LONGITUDINAL CHARACTER- 
ISTICS OF A THIN UNSWEPT-WING MODEL 
EQUIPPED WITH LEADING- AND TRAILING-EDGE 

FLAPS. David G. Koenig. July 1956. 52p. 
diagrs., photo., tabs. (NACA RM A56D23) 



LOW-SPEED WIND-TUNNEL RESULTS FOR A THIN 
ASPECT -RATIO- 1.8 5 POINT ED -WING-FUSELAGE 
MODEL WITH DOUBLE SLOTTED FLAPS. Albert 
E. Brown. July 1956. 31p. diagrs., tabs. 
(NACA RM L56D03) 



BLOWING OVER THE FLAPS AND WING LEADING 
EDGE OF A THIN 49° SWEPT WING-BODY -TAIL 
CONFIGURATION IN COMBINATION WITH LEADING- 
EDGE DEVICES. H. Clyde McLemore and Marvin P. 
Fink. July 1956. 57p. diagrs., photo. 
(NACA RM L56E16) 



HINGE MOMENT AND EFFECTr/ENESS OF AN 
UNSWEPT CONSTANT -CHORD CONTROL AND AN 
OVERHANG-BALANCED, SWEPT HINGE -LINE 
CONTROL ON AN 8(P SWEPT POINTED WING AT 
MACH NUMBERS FROM 0.75 TO 1.96. Lawrence D. 
Guy. August 1956. 39p. diagrs., photo. 
(NACA RM L53F11) 



FREE-FLIGHT INVESTIGATION OVER A MACH 
NUMBER RANGE FROM 0.74 TO 1.43 AT LIFT CO- 
EFFICIENTS FROM -0.15 TO 0.75 OF AN AIRPLANE- 
CONFIGURATION MODEL HAVING A 52.5<> DELTA 
WING AND A LOW SWEPT HORIZONTAL TAIL. 
Alan B. Kehlet. September 1956. 41p. diagrs., 
photos. (NACA RM L56G09) 



FULL-SCALE WIND-TUNNEL TESTS OF A 35° 
SWEPTBACK-WING AIRPLANE WITH HIGH- 
VELOCITY BLOWING OVER THE TRAILING-EDGE 
FLAPS - LONGITUDINAL AND LATERAL STABIL- 
ITY AND CONTROL. William H. Tolhurst, Jr., 
and Mark W. Kelly. October 1956. 64p. diagrs., 
photo., tabs. (NACA RM A56E24) 



LARGE-SCALE WIND-TUNNEL TESTS OF AN AIR- 
PLANE MODEL WITH A 450 SWEPTBACK WING OF 
ASPECT RATIO 2.8 WITH AREA SUCTION APPLIED 
TO TRAILING-EDGE FLAPS AND WITH SEVERAL 
WING LEADING-EDGE MODIFICATIONS. David G. 
Koenig and Kiyoshi Aoyagl. November 1956. 66p. 
diagrs.. photo., tabs. (NACA RM A56H08) 



AN ANALYSIS OF THE EFFECTS OF AEROELAS- 
TICITY ON STATIC LONGITUDINAL STABILITY 
AND CONTROL OF A SWEPT -WING AIRPLANE. 
Richard B. Skoog. 1957. ii, 12p. diagrs. 
(NACARept. 1298. Supersedes RM A51C19) 



EXPERIMENTAL AND PREDICTED LONGITUDINAL 
AND LATERAL-DIRECTIONAL RESPONSE CHAR- 
ACTERISTICS OF A LARGE FLEXIBLE 35° SWEPT - 
WTNG AIRPLANE AT AN ALTITUDE OF 35,000 FEET. 
Henry A. Cole, Jr., Stuart C. Brown, and Euclid C. 
Holleman. 1957. ii, 39p, diagrs., photo., tabs. 
(NACA Rept. 1330. Supersedes RM A54H09; 
TN 3874) 



165 



(1) AERODYNAMICS 



THE SUBSONIC STATIC AERODYNAMIC CHARAC- 
TERISTICS OF AN AIRPLANE MODEL HAVING A 
TRIANGULAR WING OF ASPECT RATIO 3. I - EF- 
FECTS OF HORIZONTAL -TAIL LOCATION AND 
SIZE ON THE LONGITUDINAL CHARACTERISTICS. 
Bruce E. Tinling and Armando E. Lopez. July 1957. 
85p, diagrs., photo., tabs. (NACATN4041. Super- 
sedes RM A53H 5) 



THE SUBSONIC STATIC AERODYNAMIC CHARAC- 
TERISTICS OF AN AIRPLANE MODEL HAVING A 
TRIANGULAR WING OF ASPECT RATIO 3. 
DJ - EFFECTS OF TRAILING-EDGE FLAPS. Bruce 

E. Tinling and A. V. Karpen. July 1957. 37p. 
diagrs., photos., tabs. (NACATN4043. Super- 
sedes RM A54L07) 



GROUND EFFECTS ON THE LONGITUDINAL CHAR- 
ACTERISTICS OF TWO MODELS WITH WINGS 
HAVING LOW ASPECT RATIO AND POINTED TIPS. 
Donald A. Buell and Bruce E . Tinling. July 1957. 
48p. diagrs., photos., tabs. (NACA TN 4044. 
Supersedes RM A55E04) 



REVIEW AND INVESTIGATION OF UNSATISFACTO- 
RY CONTROL CHARACTERISTICS INVOLVING IN- 
STABILITY OF PILOT-AIRPLANE COMBINATION 
AND METHODS FOR PREDICTING THESE DIFFI- 
CULTIES FROM GROUND TESTS. William H. 
Phillips, B. Porter Brown, and James T. Matthews, 
Jr. August 1957. 57p. diagrs. (NACA TN 4064. 
Supersedes RM L53F17a) 



FUG HT -TEST INVESTIGATION ON THE LANG LEY 
CONTROL-LINE FACILITY OF A MODEL OF A 
PROPELLER -DRIVEN TAIL -SITTER -TYPE 
VERTICAL -TAKE -OFF AIRPLANE WITH DELTA 
WING DURING RAPID TRANSITIONS. Robert O- 
Schade. August 1957. 19p. diagrs., photo., tab. 
(NACA TN 4070) 



WIND-TUNNEL INVESTIGATION OF EXTERNAL- 
FLOW JET-AUGMENTED DOUBLE SLOTTED 
FLAPS ON A RECTANGULAR WING AT AN ANGLE 
OF ATTACK OF 0° TO HIGH MOMENTUM COEFFI- 
CIENTS. Edwin E. Davenport. September 1957. 
31p. diagrs., tabs. (NACA TN 4079) 



WIND-TUNNEL INVESTIGATION AT LOW SPEEDS 
TO DETERMINE FLOW-FIELD CHARACTERISTICS 
AND GROUND INFLUENCE ON A MODEL WITH 
JET-AUGMENTED FLAPS. Raymond D. Vogler and 
Thomas R. Turner. September 1957. 48p. diagrs., 
photos- (NACA TN 4116) 



TRANSITION-FLIGHT INVESTIGATION OF A 
FOUR-ENGINE-TRANSPORT VERTICAL-TAKE- 
OFF AIRPLANE MODEL UTILIZING A LARGE 
FLAP AND EXTENSIBLE VANES FOR REDIRECT- 
ING THE PROPELLER SLIPSTREAM. Louis P. 
Tosti. December 1957. 35p. diagrs., photos., 
tab., film suppl. available on request. 
(NACA TN 4131) 



AN ANALYTICAL INVESTIGATION OF THE GUST- 
ALLEVIATING PROPERTIES OF A SIMPLE PITCH 
DAMPER. Norman L. Crabill. December 1957. 
47p. diagrs., tab. (NACA TN 4173) 



THREE-DEGREE-OF-FREEDOM EVALUATION 
OF THE LONGITUDINAL TRANSFER FUNCTIONS 
OF A SUPERSONIC CANARD MISSILE CONFIGU- 
RATION INCLUDING CHANGES IN FORWARD 
SPEED. Ernest C. Seaberg. December 1957. 
29p. diagrs., photo., tabs. (NACA TN 4192. 
Supersedes RM L54C02) 



GROUND SIMULATOR STUDIES OF THE EFFECTS 
OF VALVE FRICTION, STICK FRICTION, FLEXI- 
BILITY AND BACKLASH ON POWER CONTROL 
SYSTEM QUALITY. B. Porter Brown. 1958. 11, 
13p. diagrs., photo. (NACA Rept. 1348. Super- 
sedes TN 3998) 



LOW-SPEED BOUNDARY-LAYER-CONTROL 
INVESTIGATION ON A THIN RECTANGULAR SEMI- 
SPAN WING WITH LEADING-EDGE AND TRAILING- 
EDGE FLAPS. Delwin R. Croom and Thomas R. 
Turner. January 1958. 21 3p. diagrs., tabs. 
(NACARML57J1M 



WIND-TUNNEL INVESTIGATION OF THE STATIC 
LONGITUDINAL STABILITY AND TRIM CHARAC- 
TERISTICS OF A SWEPTBACK-WING JET- 
TRANSPORT MODEL EQUD7PED WITH AN 
EXTERNAL-FLOW JET-AUGMENTED FLAP. 
Joseph L. Johnson, Jr. January 1958. 89p. 
diagrs., tab. (NACA TN 4177) 



ANALYTICAL INVESTIGATION OF ACCELERA- 
TION RESTRICTION IN A FIGHTER AIRPLANE 
WITH AN AUTOMATIC CONTROL SYSTEM. 
James T. Matthews, Jr. January 1958. 24p. 
diagrs. (NACA TN 4179) 



MEASURED AND PREDICTED DYNAMIC RESPONSE 
CHARACTERISTICS OF A FLEXIBLE AIRPLANE TO 
ELEVATOR CONTROL OVER A FREQUENCY RANGE 
INCLUDING THREE STRUCTURAL MODES. 
Henry A. Cole, Jr., and Euclid C. Holleman. 
February 1958. 81p. diagrs., photo., tabs. 
(NACA TN 4147) 



QUALITATIVE SIMULATOR STUDY OF LONGITU- 
DINAL STICK FORCES AND DISPLACEMENTS 
DESIRABLE DURING TRACKING. Stanley Faber. 
February 1958. 23p. diagrs., photo. 
(NACA TN 4202) 



DATA FROM FLOW-FIELD SURVEYS BEHIND A 
LARGE-SCALE THIN STRAIGHT WING OF ASPECT 
RATIO 3, William T. Evans. June 1958. 13p. 
diagrs. (NACA RM A58D17) 



EXPLORATORY WIND-TUNNEL INVESTIGATION TO 
DETERMINE THE LIFT EFFECTS OF BLOWING 
OVER FLAPS FROM NACELLES MOUNTED ABOVE 
THE WING. John M. Riebe and Edwin E. Davenport. 
June 1958. 19p. diagrs., tab. (NACA TN 4298) 



WIND-TUNNEL INVESTIGATION AT LOW SPEEDS 
OF FLIGHT CHARACTERISTICS OF A SWEPTBACK- 
WING JET-TRANSPORT AIRPLANE MODEL 
EQUIPPED WITH AN EXTERNAL-FLOW JET- 
AUGMENTED SLOTTED FLAP. Joseph L. Johnson, 
Jr. July 1958. 32p. diagrs., photos., tab., film 
suppl. available on request. (NACA TN 4255) - 



EXPLORATORY WIND -TUNNEL INVESTIGATION 
AT HIGH SUBSONIC AND TRANSONIC SPEEDS OF 

JET FLAPS ON UNSWEPT RECTANGULAR WINGS. 
Vernard E. Lockwood and Raymond D. Vogler 
August 1958. 37p. diagrs. (NACA TN 4353) 



SOME STATIC LONGITUDINAL STABILITY CHAR- 
ACTERISTICS OF AN OVERLAPPED-TYPE TANDEM- 
ROTOR HELICOPTER AT LOW AIRSPEEDS. Robert 
J, Tapscott, September 1958. 27p. diagrs., tabs. 
(NACA TN 4393) 



166 



(1) AERODYNAMICS 



EFFECTS OF PROPELLER POSITION AND OVER- 
LAP ON THE SUPSTREAM DEFLECTION CHAR- 
ACTERISTICS OF A WING-PROPELLER CONFIG- 
URATION EQUD7PED WITH A SLIDING AND 
FOWLER FLAP. William C. Hayes, Jr., Richard E. 
Kuhn, and Irving R. Sherman. September 1958. 
81p. diagrs., photos. (NACA TN 4404) 



(1.8.2.2) 

LATERAL 



LATERAL STABILITY AND CONTROL CHARACTER- 
ISTICS OF AN AIRPLANE MODEL HAVING A 42.8° 
SWEPTBACK CIRCULAR-ARC WING WITH ASPECT 
RATIO 4.00, TAPER RATIO 0.50, AND SWEPTBACK 
TAIL SURFACES. Kenneth W. Goodson and Paul 
Comisarow. October 17, 1947. 72p. diagrs., 
photos., tab. (NACA RM L7G31) 



PRELIMINARY INVESTIGATION AT A MACH NUM- 
BER OF 1.9 AND A REYNOLDS NUMBER OF 
2,200,000 OF THREE AILERONS APPUCABLE TO 
THE BELL XS-2 AffiPLANE DESIGN. James C. 
Sivells and D. William Conner. May 25, 1948. 
lip. diagrs., tab. (NACA RM L8D02) 



ESTIMATED TRANSONIC FLYING QUALITIES OF A 
TAILLESS AIRPLANE BASED ON A MODEL INVES- 
TIGATION. Charles J. Donlan and Richard E. Kuhn. 
June 8, 1949. 63p. diagrs., photos., tabs. 
(NACA RM L9D08) 



INVESTIGATION OF THE DYNAMIC LATERAL 
STABILITY AND CONTROL CHARACTERISTICS OF 
A MODEL OF A FIGHTER AIRPLANE WITHOUT A 
HORIZONTAL TAIL AND EQUIPPED WITH EITHER 
SINGLE OR TWIN VERTICAL TAILS. John W. 
Draper and Robert W. Rose. November 15, 1949. 
20p. diagrs., photos., tab. (NACA RM L9J07a) 



AERODYNAMIC STUDY OF A WING -FUSELAGE 
COMBINATION EMPLOYING A WING SWEPT BACK 
63°. - EFFECTS AT SUBSONIC SPEEDS OF A 
CONSTANT-CHORD ELEVON ON A WING CAM- 
BERED AND TWISTED FOR A UNIFORM LOAD AT 
A LIFT COEFFICIENT OF 0.25. J. Lloyd Jones and 
Fred A. Demele. December 5, 1949. 44p. diagrs., 
photos., tab. (NACA RM A9I27) 



WIND-TUNNEL TESTS OF A 0.16-SCALE MODEL 
OF THE X-3 AIRPLANE AT HIGH SUBSONIC SPEEDS. 
- ADDITIONAL STABILITY AND CONTROL CHAR- 
ACTERISTICS AND THE AERODYNAMIC EFFECTS 
OF EXTERNAL STORES AND RAM JETS. Joseph W. 
Cleary and Jack A. Mellenthin. June 13,- 1950. 86p. 
diagrs., photos., tabs. (NACA RM A50C30) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR -ARC SECTIONS AND 40° SWEEPBACK. 
STATIC LATERAL CONTROL CHARACTERISTICS 
AT MACH NUMBERS OF 1.40 AND 1.59. Ross B. 
Robinson. November 10, 1950. 40p. diagrs., 
photos., tabs. (NACA RM L50I11) 



AN INVESTIGATION AT MACH NUMBERS OF 1.40 
AND 1.59 OF THE EFFECTS OF AILERON PROFILE 
ON THE AERODYNAMIC CHARACTERISTICS OF A 
COMPLETE MODEL OF A SUPERSONIC AIRCRAFT 
CONFIGURATION. M. Leroy Spearman and Robert 
A. Webster. January 15, 1951. 40p. diagrs., 
photos., tabs. (NACA RM L50J31) 



FREE-FLIGHT MEASUREMENTS AT MACH NUM- 
BERS FROM 0.7 TO 1.6 OF SOME EFFECTS OF 
AIRFOIL-THICKNESS DISTRIBUTION AND 
TRAILING-EDGE ANGLE ON AILERON ROLLING 
EFFECTIVENESS AND DRAG FOR WINGS WITH 0° 
AND 45° SWEEPBACK. E. M. Fields and H. Kurt 
Strass. October 1951. 63p. diagrs., photos., tab. 
(NACA RM L51G27) 



SUMMARY OF SOME EFFECTIVE AERODYNAMIC 
TWISTING -MOMENT COEFFICIENTS OF VARIOUS 
WING-CONTROL CONFIGURATIONS AT MACH 
NUMBERS FROM 0.6 TO 1.7 AS DETERMINED 
FROM ROCKET-POWERED MODELS. H. Kurt 
Strass. January 1952. 22p. diagrs., photo., 
2 tabs. (NACA RM L51K20) 



THE AERODYNAMIC CHARACTERISTICS OF A 
SUPERSONIC AIRCRAFT CONFIGURATION WITH A 
40° SWEPTBACK WING THROUGH A MACH NUM- 
BER RANGE FROM TO 2.4 AS OBTAINED FROM 
VARIOUS SOURCES. M. Leroy Spearman and Ross 
B. Robinson. April 1952. 50p. diagrs., photo., 
tab. (NACA RM L52A21) 



FREE -FLIGHT MEASUREMENTS OF SOME EF- 
FECTS OF SPOILER SPAN AND PROJECTION AND 
WING FLEXIBILITY ON ROLLING EFFECTP/ENESS 
AND DRAG OF PLAIN SPOILERS ON A TAPERED 
SWEPTBACK WING AT MACH NUMBERS BETWEEN 
0.6 AND 1.6. Eugene D. SchultandE, M. Fields. 
October 1952. 30p. diagrs., photo., tab. 
(NACA RM L52H06a) 



HINGE -MOMENT CHARACTERISTICS FOR SEVER- 
AL TIP CONTROLS ON A 60° SWEPTBACK DELTA 
WING AT MACH NUMBER 1.61. K. R. Czarnecki 
and Douglas R. Lord. January 1953. 31p. diagrs., 
photos. (NACA RM L52K28) 



A THEORETICAL STUDY OF THE EFFECT OF 
CONTROL -DE FLECTION AND CONTROL-RATE 
LIMITATIONS ON THE NORMAL ACCELERATION 
AND ROLL RESPONSE OF A SUPERSONIC INTER- 
CEPTOR. Howard F. Matthews and Stanley F, 
Schmidt. April 1953. 28p. photos., diagrs., 
tabs. (NACA RM A53B11) 



LOADS DUE TO FLAPS AND SPOILERS ON SWEPT- 
BACK WINGS AT SUPERSONIC AND TRANSONIC 
SPEEDS. Alexander D. Hammond and F . E. West, 
Jr. June 1953. 17p. diagrs. (NACA RM L53D29a) 



A STUDY OF VISUAL INTERCEPTION ATTACKS 
ON A NONMANEUVERING AIRPLANE TARGET. 
Donald C. Cheatham, Charles W. Mathews, and 
John A. Harper. July 1953, 97p. diagrs., photos., 
tabs. (NACA RM L53E01) 



INVESTIGATION OF SPOILER AILERONS WITH AND 
WITHOUT A GAP BEHIND THE SPOILER ON A 45° 
SWEPTBACK WING-FUSELAGE COMBINATION AT 
MACH NUMBERS FROM 0.60 TO 1.03. F. E. West, 
Jr., William Solomon, and Edward M. Brummal. 
September 1953. 38p. diagrs. (NACA RM L53G07a) 



SUBSONIC AMD SUPERSONIC HINGE-MOMENT AND 
EFFECTIVENESS CHARACTERISTICS OF AN UN- 
BALANCED LATERAL CONTROL HAVING LOW 
THEORETICAL HINGE MOMENTS AT SUPERSONIC 
SPEEDS. Kennith L. Goin and William E. Palmer. 
October 1953. 55p. diagrs., photos. 
(NACA RM L53G3U) 



167 



(1) AERODYNAMICS 



RECENT EXPERIENCES WITH FLUTTER FAILURE 
OF SWEPTBACK, TAPERED WINGS HAVING OUT- 
BOARD, PARTIAL-SPAN SPOILER CONTROLS. 
H. Kurt Strass and Edward T. Mar ley. October 
1953. 20p. diagrs., photos., tabs. 
(NACA.RM L53H26) 



DATA ON SPOILER-TYPE AILERONS. 
Lowry. October 1953. 27p. diagrs. 
(NACA RM L53I24a) 



John G. 



A METHOD FOR ESTIMATING THE ROLLING MO- 
MENTS CAUSED BY WING-TAIL INTERFERENCE 
FOR MISSILE AT SUPERSONIC SPEEDS. Sherman 
Edwards and Katsumi Hikido. November 1953. 68p 
diagrs., tabs. (NACA RM A53H18) 



AN ENGINEERING METHOD FOR THE DETER- 
MINATION OF AEROELASTIC EFFECTS UPON THE 
ROLLING EFFECTIVENESS OF AILERONS ON 
SWEPT WINGS. H. Kurt Strass and Emily W- 
Stephens. November 1953. 82p. diagrs., tabs. 
(NACA RM L53H14) 



LOW-SPEED STATIC STABILITY AND CONTROL 
CHARACTERISTICS OF A I/4-SCALE MODEL OF 
THE BELL X-l AIRPLANE EQUIPPED WITH A 
4-PERCENT -THICK, ASPECT-RATIO-4, UNSWEPT 
WING. William C. Moseley, Jr., and Robert T. 
Taylor. November 1953. 53p. uiagra., photos., 
tab. (NACA RM L53H27) 



CONTROL HTNGE-MOMENT AND EFFECTIVENESS 
CHARACTERISTICS OF SEVERAL INTERCHANGE- 
ABLE TIP CONTROLS ON A 60° DELTA WING AT 
MACH NUMBERS OF 1.41, 1.62, AND 1.96. Odell 
A. Morris. November 1953. 33p. diagrs., photo., 
tab. (NACA RM L53J08a) 



EFFECT OF LARGE DEFLECTIONS OF A CANARD 
CONTROL AND DEFLECTIONS OF A WING-TIP 
CONTROL ON THE STATIC-STABILITY AND 
INDUCED-ROLL CHARACTERISTICS OF A CRUCI- 
FORM CANARD MISSILE AT A MACH NUMBER OF 
2.01. M. Leroy Spearman. December 1953. 20p. 
diagrs., tabs. (NACA RM L53K03) 



WIND-TUNNEL INVESTIGATIONS AT LOW AND 
TRANSONIC SPEEDS OF THE FEASIBILITY OF 
SELF-ACTUATING SPOILERS AS A LATERAL- 
CONTROL DEVICE FOR A MISSILE. Harleth G. 
Wiley and William C. Hayes, Jr. January 1954. 
24p. diagrs., tab. (NACA RM L53K27) 



AERODYNAMIC CHARACTERISTICS OF A FULL- 
SPAN TRAILING-EDGE CONTROL ON A 60° DELTA 
WING WITH AND WITHOUT A SPOILER AT MACH 
NUMBER 1.61. Douglas R. LordandK. R. 
Czarnecki. March 1954. 49p. diagrs., photos., 
tab. (NACA RM L53L17) 



EFFECTS OF SPOILER AILERONS ON THE AERO- 
DYNAMIC LOAD DISTRIBUTION OVER A 45° 
SWEPTBACK WING AT MACH NUMBERS FROM 0.60 
TO 1.03. Joseph M. Hallissy, Jr., F. E. West, Jr., 
and George Liner. May 1954. 162p. diagrs., tabs. 
(NACARM L54C17a) 



AERODYNAMIC CHARACTERISTICS OF SEVERAL 
TIP CONTROLS ON A 60° DELTA WING AT A MACH 
NUMBER OF 1.61. Douglas R. Lord and K. R. 
Czarnecki. August 1954. 44p. diagrs., photos., 
tabs. (NACA RM L54E25) 



EFFECTS OF OVERHANG BALANCE ON THE 
HINGE-MOMENT AND EFFECTIVENESS CHARAC- 
TERISTICS OF AN UNSWEPT TRAILING-EDGE 
CONTROL ON A 60° DELTA WING AT TRANSONIC 
AND SUPERSONIC SPEEDS. Lawrence D. Guy. 
September 1954. 48p. diagrs., photo. 
(NACA RML54G12a) 



SOME EFFECTS OF AILERON SPAN, AILERON 
CHORD, AND WING TWIST ON ROLLING EFFEC- 
TIVENESS AS DETERMINED BY ROCKET- 
POWERED MODEL TESTS AND THEORETICAL 
ESTIMATES. H. Kurt Strass and Warren A. Tucker. 
September 1954. 29p. diagrs., photos., tabs. 
(NACA RM L54G13) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR-ARC SECTIONS AND 40° SWEEPBACK. 
STATIC LONGITUDINAL AND LATERAL STABILITY 
AND CONTROL CHARACTERISTICS AT A MACH 
NUMBER OF 1.89. M. Leroy Spearman and Edward 
B. Palazzo. October 1954. 24p. diagrs., photo., 
tab. (NACA RM L54G26a) 



FREE -FLIGHT MEASUREMENTS OF THE ROLLING 
EFFECTIVENESS AND OPERATING CHARACTER- 
ISTICS OF A BELLOWS-ACTUATED SPLIT-FLAP 
AILERON ON A 60° DELTA WING AT MACH NUM- 
BERS BETWEEN 0.8 AND 1.8. Eugene D. Schult. 
October 1954. 33p. diagrs., photos. 
{NACA RM L54K17) 



THE EFFECT OF AN OPERATING PROPELLER ON 
THE AERODYNAMIC CHARACTERISTICS AT HIGH 
SUBSONIC SPEEDS OF A MODEL OF A VERTICAL- 
RISING AIRPLANE HAVING AN UNSWEPT WTNG OF 
ASPECT RATIO 3. Fred B. Sutton and Donald A. 
Buell. November 1954. 90p. diagrs., photos., 
tabs. (NACA RM A52E06) 



COMPARISON OF EFFECTS OF AILERONS AND 
COMBINATIONS OF SPOILER-SLOT-DEFLECTOR 
ARRANGEMENTS ON SPIN RECOVERY OF SWEPT- 
BACK-WING MODEL HAVING MASS DISTRIBUTED 
ALONG THE FUSELAGE. Frederick M. Heaiy and 
Walter J. Klinar. November 1954. 18p. diagrs., 
photo., tabs. (NACA RM L54I14) 



LATERAL MOTIONS ENCOUNTERED WITH THE 
DOUGLAS D-558-II ALL-ROCKET RESEARCH AIR- 
PLANE DURING EXPLORATORY FLIGHTS TO A 
MACH NUMBER OF 2.0. Herman O. Ankenbruck 
and Chester H. Wolowicz. December 1954. 32p. 
diagrs., photos., tab. (NACA RM H54I27) 



ROLLING PERFORMANCE OF THE REPUBLIC 
YF-84F AIRPLANE AS MEASURED IN FLIGHT. 
John B. McKay. January 1955. 24p. diagrs., 
photo., tab. (NACA RM H54G20a) 



EFFECTS OF A DETACHED TAB ON THE HTNGE- 
MOMENT AND EFFECTIVENESS CHARACTER- 
ISTICS OF AN UNSWEPT TRAILING-EDGE CON- 
TROL ON A 60° DELTA WING AT MACH NUMBERS 
FROM 0.75 TO 1.96. Odell A. Morris and 
Gertrude C. West rick. April 1955. 36p. diagrs., 
photo. (NACA RM L55B15) 



LATERAL STABILITY AND CONTROL CHARACTER- 
ISTICS OF THE CONVAIR XF-92A DELTA-WING 
AIRPLANE AS MEASURED IN FLIGHT. Thomas R. 
Sisk andDuane O- Muhleman. May 1955. 55p. 
diagrs., photos., tabs. (NACA RM H55A17) 



168 



(1) AERODYNAMICS 



EFFECT OF A WING LEADING -EDGE FLAP AND 
CHORD-EXTENSION ON THE HIGH SUBSONIC 
CONTROL CHARACTERISTICS OF AN AILERON 
LOCATED AT TWO SPANWISE POSITIONS. Robert 
F. Thompson and Robert T. Taylor. May 1955. 
59p. diagrs., photo., tabs. (NACA RM L55B18at 



STABILITY AND CONTROL CHARACTERISTICS 
OBTAINED DURING DEMONSTRATION OF THE 
DOUGLAS X-3 RESEARCH AIRPLANE. Richard E. 
Day and Jack Fischel. July 1955. 51p. diagrs., 
photos., tab. (NACA RM H55E16) 



SIMULATOR STUDIES OF THE ATTACK PHASE OF 
AN AUTOMATICALLY CONTROLLED INTERCEP- 
TOR. I - PRELIMINARY STUDIES OF THE LATER- 
AL AND LONGITUDINAL CONTROL SYSTEMS. 
Albert A. Schy, Ordway B. Gates, Jr., and C. H. 
Woodling. II - SOME RESULTS OF A STUDY PER- 
FORMED ON THE TYPHOON COMPUTER. Windsor 
L. Sherman and Leonard Sternfield. August 1955. 
24p. diagrs. (NACA RM L55E27a) 



COLLECTION AND SUMMARY OF FLAP-TYPE- 
AILERON ROLLING-EFFECTIVENESS DATA AT 
ZERO LIFT AS DETERMINED BY ROCKET- 
POWERED MODEL TESTS AT MACH NUMBEFLS 
BETWEEN 0.6 AND 1.6. H. Kurt Strass, Emily W. 
Stephens, E. M. Fields, and Eugene D. Schult. 
September 1955. 95p. diagrs., photos., tabs. 
(NACA RM L55F14) 



WIND-TUNNEL INVESTIGATION AT TRANSONIC 
SPEEDS OF A JET CONTROL ON AN 80° DELTA- 
WING MISSILE. Thomas R. Turner and Raymond D. 
Vogler. November 1955. 32p. diagrs. 
(NACA RM L55H22) 



LOW -SPEED PRESSURE -DISTRIBUTION INVESTI- 
GATION OF A SPOILER AND A SPOILER-SLOT- 
DEFLECTOR ON A 30° SWEPTBACK WING- 
FUSELAGE MODEL HAVING AN ASPECT RATIO 
OF 3, A TAPER RATIO OF 0.5, AND NACA 65A004 
AIRFOIL SECTION. Alexander D. Hammond. 
January 1956. 176p. diagrs., tabs. 
(NACA RM L55I29) 



WIND-TUNNEL INVESTIGATION AT TRANSONIC 
SPEEDS OF A JET CONTROL ON A 35° SWEPT 
WING. TRANSONIC -BUMP METHOD. Raymond D. 
Vogler and Thomas R. Turner. February 1956. 
17p. diagrs. (NACA RM L55K09) 



SOME EFFECTS OF AILERONS ON THE VARIATION 
OF AERODYNAMIC CHARACTERISTICS WITH SIDE- 
SLIP AT LOW SPEED. Kenneth W. Goqdson. 
March 1956. 4 Op. diagrs., tab. (NACA RM L55L20) 



AN ANALOG STUDY OF THE RELATIVE IMPOR- 
TANCE OF VARIOUS FACTORS AFFECTING ROLL 
COUPLING. Joseph Weil and Richard E . pay. 
April 1956. 81p. diagrs., photo., tabs. 
(NACA RM H56A06) 



FREE-FLIGHT INVESTIGATION OF THE CONTROL 
EFFECTIVENESS OF A DIFFERENTIALLY DE- 
FLECTED HORIZONTAL TAIL AT MACH NUMBERS 
FROM 0.8 TO 1.6. Jesse L. Mitchell and A. James 
Vitale. April 1956. 25p. diagrs., photo., tabs. 
(NACA RM L56B20) 



BLOWING OVER THE FLAPS AND WING LEADING 
EDGE OF A THIN 49<> SWEPT WING-BODY-TAIL 
CONFIGURATION IN COMBINATION WITH LEADING- 
EDGE DEVICES. H. Clyde McLemore and Marvin P. 
Fink. July 1956. 57p. diagrs., photo. 
(NACA RM L56E16) 



WIND-TUNNEL INVESTIGATION AT HIGH SUBSONIC 
SPEEDS OF JET, SPOILER, AND AILERON CON- 
TROLS ON A 1/16-SCALE MODEL OF THE DOUGLAS 
D-558-H RESEARCH AIRPLANE . Raymond D . 
Vogler. July 1956. 52p. diagrs., photo., tabs. 
(NACA RM L56E25) 



HINGE MOMENT AND EFFECTIVENESS OF AN 
UNSWEPT CONSTANT -CHORD CONTROL AND AN 
OVERHANG-BALANCED, SWEPT HINGE-LINE 
CONTROL ON AN 80<> SWEPT POINTED WING AT 
MACH NUMBERS FROM 0.75 TO 1.96. Lawrence D. 
Guy. August 1956. 39p. diagrs., photo. 
(NACARM L56FU) 



LOW-SPEED INVESTIGATION OF THE LATERAL- 
CONTROL CHARACTERISTICS OF A FLAP-TYPE 
SPOILER AND A SPOILER-SLOT-DEFLECTOR ON 
A 30° SWEPTBACK WING-FUSELAGE MODEL 
HAVING AN ASPECT RATIO OF 3, A TAPER RATIO 
OF 0.5, AND NACA 65A004 AIRFOIL SECTION. 
Alexander D. Hammond. August 1956. 25p. diagrs., 
tab. (NACA RM L56F18) 



FULL-SCALE WIND-TUNNEL TESTS OF A 35° 
SWEPTBACK-WING AIRPLANE WITH HIGH- 
VELOCITY BLOWING OVER THE TRAILmG-EDGE 
FLAPS - LONGITUDINAL AND LATERAL STABIL- 
ITY AND CONTROL. William H. Tolhurst, Jr., 
and Mark W. Kelly. October 1956. 64p. diagrs., 
photo., tabs. (NACA RM A56E24) 



THE EFFECT OF EXTERNAL STIFFENING RIBS ON 
THE ROLLING POWER OF AILERONS ON A SWEPT 
WING. Emily W. Stephens. October 1956. 15p. 
diagrs., photo., tab. (NACA RM L56D19) 



FORCE TEST RESULTS FOR BODY-MOUNTED 
LATERAL CONTROLS AND SPEED BRAKES ON A 
45° SWEPT-WING MODEL AT MACH NUMBERS 
FROM 0.80 TO 0.98. F. E. West, Jr., and Chris C. 
Critzos. December 1956. 32p. diagrs., photos., 
tab. (NACA RM L56I05) 



FLIGHT INVESTIGATION OF THE EFFECTIVENESS 
OF AN AUTOMATIC AILERON TRIM CONTROL 
DEVICE FOR PERSONAL AIRPLANES. William H. 
Phillips, Helmut A. Kuehnel, and James B. Whitten. 
1957. ii, 15p. diagrs., photos. 
(NACA Rept. 1304. Supersedes TN 3637) 



EXPERIMENTAL AND PREDICTED LONGITUDINAL 
AND LATERAL-DIRECTIONAL RESPONSE CHAR- 
ACTERISTICS OF A LARGE FLEXIBLE 35° SWEPT- 
WING AIRPLANE AT AN ALTITUDE OF 35,000 FEET. 
Henry A. Cole, Jr., Stuart C. Brown, and Euclid C. 
Holleman. 1957. ii, 39p. diagrs., photo., tabs. 
(NACA Rept. 1330. Supersedes RM A54H09; 
TN 3874) 



( 1 ) AERODYNAMICS 



169 



THE SUBSONIC STATIC AERODYNAMIC CHARAC- 
TERISTICS OF AN AIRPLANE MODEL HAVING A 
TRIANGULAR WING OF ASPECT RATIO 3. 
m - EFFECTS OF TRAILING -EDGE FLAPS. Bruce 
E. Tinling and A. V. Karpen. July 1957. 37p. 
diagrs., photos., tabs. (NACA TN 4043. Super- 
sedes RM A54L07) 



THE SUBSONIC STATIC AERODYNAMIC CHARAC- 
TERISTICS OF AN AIRPLANE MODEL HAVING A 
TRIANGULAR WING OF ASPECT RATIO 3. 
H - LATERAL AND DIRECTIONAL CHARACTERIS- 
TICS. Howard F. Savage and Bruce E. Tinling. 
August 1957. 82p. diagrs., photo., tabs. 
(NACA TN 4042. Supersedes RM A55B11) 



TRANSITION-FLIGHT INVESTIGATION OF A 
FOUR-ENGINE -TRANSPORT VERTICAL-TAKE- 
OFF AIRPLANE MODEL UTILIZING A LARGE 
FLAP AND EXTENSIBLE VANES FOR REDIRECT- 
ING THE PROPELLER SLIPSTREAM. Louis P. 
Tosti. December 1957. 35p. diagrs., photos., 
tab., film suppl. available on request. 
(NACA TN 4131) 



A METHOD FOR THE CALCULATION OF THE 
LATERAL RESPONSE OF AIRPLANES TO RANDOM 
TURBULENCE! John M. Eggleston and William H. 
Phillips. February 1958. 34p. diagrs., tab. 
(NACA TN 4196) 



WIND-TUNNEL INVESTIGATION AT LOW SPEEDS 
OF FLIGHT CHARACTERISTICS OF A SWEPTBACK- 
WING JET -TRANSPORT AIRPLANE MODEL 
EQUIPPED WITH AN EXTERNAL -FLOW JET- 
AUGMENTED SLOTTED FLAP. Joseph L. Johnson, 
Jr. July 1958. 32p. diagrs., photos., tab., film 
suppl. available on request. (NACA TN 4255) 



(1.8.2. 3) 
DIRECTIONAL 



LATERAL STABILITY AND CONTROL CHARACTER- 
ISTICS OF AN AIRPLANE MODEL HAVING A 42.8° 
SWEPTBACK CIRCULAR-ARC WING WITH ASPECT 
RATIO 4.00, TAPER RATIO 0.50, AND SWEPTBACK 
TAIL SURFACES. Kenneth W. Goodson and Paul 
Comisarow. October 17, 1947. 72p. diagrs., 
photos., tab. {NACA RM L7G31) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR -ARC SECTIONS AND 4(P SWEEPBACK. 
STATIC LATERAL CONTROL CHARACTERISTICS 
AT MACH NUMBERS OF 1.40 AND 1.59. Ross B. 
Robinson. November 10, 1950. 40p. diagrs., 
photos., tabs. (NACA RM L50I11) 



A STUDY OF VISUAL INTERCEPTION ATTACKS 
ON A NONMANEUVERING AIRPLANE TARGET. 
Donald C. Cheatham, Charles W. Mathews, and 
John A. Harper. July 1953. 97 p. diagrs., photos., 
tabs. (NACA RM L53E01) 



LOW -SPEED STATIC STABILITY AND CONTROL 
CHARACTERISTICS OF A 1/4-SCALE MODEL OF 
THE BELL X-l AIRPLANE EQUD7PED WITH A 
4 -PERCENT-THICK, ASPECT-RATIO-4, UNSWEPT 
WING. William C. Moseley, Jr., and Robert T. 
Taylor. November 1953. 53p. diagrs., photos., 
tab. (NACA RM L53H27) 



STATIC LATERAL STABILITY CHARACTERISTICS 
OF A 1/16-SCALE MODEL OF THE DOUGLAS 
D- 558-11 RESEARCH AIRPLANE AT MACH NUM- 
BERS OF 1.61 AND 2.01. Frederick C. Grant and 
Ross B. Robinson. November 1953. 39p. diagrs., 
photo., tabs. (NACA RM L53I29a) 



EFFECT OF LARGE DEFLECTIONS OF A CANARD 
CONTROL AND DEFLECTIONS OF A WING-TB? 
CONTROL ON THE STATIC -STABILITY AND 
INDUCED -ROLL CHARACTERISTICS OF A CRUCI- 
FORM CANARD MISSILE AT A MACH NUMBER OF 
2.01. M. Leroy Spearman. December 1953. 20p. 
diagrs., tabs. (NACA RM L53K03) 



EFFECTS OF CANOPY, REVISED VERTICAL TAIL, 
AND A YAW-DAMPER VANE ON THE AERODYNAM- 
IC CHARACTERISTICS OF A 1/16-SCALE MODEL 
OF THE DOUGLAS D-558-H RESEARCH AIRPLANE 
AT A MACH NUMBER OF 2.01. Ross B. Robinson. 
August 1954. 29p. diagrs., tabs. 
(NACA RM L54F25) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR-ARC SECTIONS AND 40° SWEEPBACK. 
STATIC LONGITUDINAL AND LATERAL STABILITY 
AND CONTROL CHARACTERISTICS AT A MACH 
NUMBER OF 1.89. M. Leroy Spearman and Edward 
B. Palazzo. October 1954. 24p. diagrs., photo., 
tab. (NACA RM L54G26a) 



EXPLORATORY INVESTIGATION OF THE LOW- 
SPEED STATIC STABILITY OF A' CONFIGURATION 
EMPLOYING THREE IDENTICAL TRIANGULAR 
WING PANELS AND A BODY OF EQUAL LENGTH. 
NoelK. Delany. April 1955. 25p. diagrs., photos. 
(NACA RM A55C28) 



LATERAL STABILITY AND CONTROL CHARACTER- 
ISTICS OF THE CONVATR XF-92A DELTA- WING 
AIRPLANE AS MEASURED IN FLIGHT. Thomas R. 
Sisk and Duane O. Muhleman. May 1955. 55p. 
diagrs., photos., tabs. (NACA RM H55A17) 



STABILITY AND CONTROL CHARACTERISTICS 
OBTAINED DURING DEMONSTRATION OF THE 
DOUGLAS X-3 RESEARCH AIRPLANE. Richard E. 

Day and Jack Fischel. July 1955. 51p. diagrs., 
photos., tab. (NACA RM H55E16) 



FREE-FLIGHT INVESTIGATION OF THE CONTROL 
EFFECTIVENESS OF A DIFFERENTIALLY DE- 
FLECTED HORIZONTAL TAIL AT MACH NUMBERS 
FROM 0,8 TO 1.6. Jesse L. Mitchell and A. James 
Vitale. April 1956. 25p. diagrs., photo., tabs. 
(NACA RM L56B20) 



THE SUBSONIC STATIC AERODYNAMIC CHARAC- 
TERISTICS OF AN AIRPLANE MODEL HAVING A 
TRIANGULAR WING OF ASPECT RATIO 3. 
H - LATERAL AND DIRECTIONAL CHARACTERIS- 
TICS. Howard F. Savage and Bruce E. Tinling. 
August 1957. 82p. diagrs., photo., tabs. 
(NACA TN 4042. Supersedes RM A55B11) 



TRANSITION-FLIGHT INVESTIGATION OF A 
FOUR-ENGINE-TRANSPORT VERTICAL-TAKE- 
OFF AIRPLANE MODEL UTILIZING A LARGE 
FLAP AND EXTENSIBLE VANES FOR REDIRECT- 
ING THE PROPELLER SLIPSTREAM. Louis P. 
"Tosti. December 1957. 35p. diagrs., photos., 
tab., film suppl. available on request. 
(NACA TN 4131) 



170 



( 1 ) AERODYNAMICS 



SUBSONIC FLIGHT INVESTIGATION OF METHODS 
TO IMPROVE THE DAMPING OF LATERAL OSCIL- 
LATIONS BY MEANS OF A VISCOUS DAMPER IN 
THE RUDDER SYSTEM IN. CONJUNCTION WITH 
ADJUSTED HINGE-MOMENT PARAMETERS. 
Harold L. Crane, George J. Hurt, Jr., and 
John M. Elliott. January 1958. 45p. diagrs., 
photos., tab. (NACA TN 4193. Supersedes 
RM L54D09) 



INTERNAL CHARACTERISTICS AND PERFORM- 
ANCE OF SEVERAL JET DEFLECTORS AT 
PRIMARY-NOZZLE PRESSURE RATIOS UP TO 
3.0. Jack G. McArdle. June 1958. ii, 107p. 
dlaKrs., photos., tabs. (NACA TN 4264) 



(1.8.2.4) 
AIR BRAKES 



ESTIMATED TRANSONIC FLYING QUALITIES OF A 
TAILLESS AIRPLANE BASED ON A MODEL INVES- 
TIGATION. Charles J. Donlan and Richard E. Kuhn. 
June 8, 1949. 63p. diagrs., photos., tabs. 
(NACA RM L9D08) 



WIND-TUNNEL TESTS OF A 0.16-SCALE MODEL 
OF THE X-3 AIRPLANE AT HIGH SUBSONIC SPEEDS. 
- ADDITIONAL STABILITY AND CONTROL CHAR- 
ACTERISTICS AND THE AERODYNAMIC EFFECTS 
OF EXTERNAL STORES AND RAM JETS- Joseph W. 
Cleary and Jack A. MeUenthin. June 13, 1950. 86p. 
diagrs., photos., tabs. (NACA RM A50C30) 



EFFECT OF FUSELAGE AIR BRAKES ON THE 
LONGITUDINAL STABILITY CHARACTERISTICS OF 
A SWEPT -WING FIGHTER MODEL AT TRANSONIC 
SPEEDS. Donald D. Arabian. April 1956. 22p. 
diagrs., photos. (NACA RM L 56 A 2 5a) 



FORCE TEST RESULTS FOR BODY-MOUNTED 
LATERAL CONTROLS AND SPEED BRAKES ON A 
45° SWEPT-WING MODEL AT MACH NUMBERS 
FROM 0.80 TO 0.98. F. E. West, Jr., and Chris C. 
Critzos. December 1956. 32p. diagrs., photos., 
tab. (NACA RM L56I05) 



INVESTIGATION OF DEFLECTORS AS GUST ALLE- 
VIATORS ON A 0.09-SCALE MODEL OF THE BELL 
X-5 AIRPLANE WITH VARIOUS WING SWEEP 
ANGLES FROM 20° TO 60° AT MACH NUMBERS 
FROM 0.40 TO 0.90. Delwin R. Croom and Jarrett 
K. Huffman. November 1957. 28p. diagrs. 
(NACA TN 4175) 



(1.8.2.5) 
HINGE MOMENTS 



AERODYNAMIC STUDY OF A WTNG-FUSELAGE 
COMBINATION EMPLOYING A WING SWEPT BACK 
63°. . EFFECTS AT SUBSONIC SPEEDS OF A 
CONSTANT -CHORD ELEVON ON A WING CAM- 
BERED AND TWISTED FOR A UNIFORM LOAD AT 
A LIFT COEFFICIENT OF 0.25. J. Lloyd Jones and 
Fred A. Demele. December 5, 1949. 44p. diagrs., 
photos., tab. (NACA RM A9I27) 



WIND-TUNNEL TESTS OF A 0.16-SCALE MODEL 
OF THE X-3 AIRPLANE AT HIGH SUBSONIC 
SPEEDS. STABILITY AND CONTROL CHARACTER- 
ISTICS- William T. Hamilton and Joseph W. Cleary. 
April 21, 1950. 129p. diagrs., photos., tabs. 
(NACA RM A50A03) 



WIND-TUNNEL TESTS OF A 0.16-SCALE MODEL 
OF THE X-3 AIRPLANE AT HIGH SUBSONIC SPEEDS. 
- ADDITIONAL STABILITY AND CONTROL CHAR- 
ACTERISTICS AND THE AERODYNAMIC EFFECTS 
OF EXTERNAL STORES AND RAM JETS . Joseph W . 
Cleary and Jack A. MeUenthin. June 13, 1950. 86p. 
diagrs., photos., tabs. (NACA RM A50C30) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR -ARC SECTIONS AND 40° SWEEPBACK. 
STATIC LATERAL CONTROL CHARACTERISTICS 
AT MACH NUMBERS OF 1 .40 AND 1 .59 . Ross B . 
Robinson. November 10, 1950. 40p. diagrs., 
photos., tabs. (NACA RM L50I11) 



AN INVESTIGATION AT MACH NUMBERS OF 1.40 
AND 1.59 OF THE EFFECTS OF AILERON PROFILE 
ON THE AERODYNAMIC CHARACTERISTICS OF A 
COMPLETE MODEL OF A SUPERSONIC AIRCRAFT 
CONFIGURATION. M. Leroy Spearman and Robert 
A. Webster. January 15, 1951. 40p. diagrs., 
photos., tabs. (NACA RM L50J31) 



FLIGHT DETERMINATION OF THE DRAG AND 
LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS OF A ROCKET -POWERED MODEL 
OF A 60° DELTA -WING AIRPLANE FROM MACH 
NUMBERS OF 0.75 TO 1.70. Grady L. Mitcham, 
Norman L. Crabill, and Joseph E. Stevens. 
November 1951. 44p. diagrs., photos., tab. 
(NACA RM L51I04) 



THE AERODYNAMIC CHARACTERISTICS OF A 
SUPERSONIC AIRCRAFT CONFIGURATION WITH A 
40° SWEPTBACK WING THROUGH A MACH NUM- 
BER RANGE FROM TO 2.4 AS OBTAINED FROM 
VARIOUS SOURCES. M. Leroy Spearman and Ross 
B. Robinson. April 1952. 50p. diagrs., photo., 
tab. (NACA RM L52A21) 



HINGE -MOMENT CHARACTERISTICS FOR SEVER- 
AL TIP CONTROLS ON A 60° SWEPTBACK DELTA 
WING AT MACH NUMBER 1.61. K. R. Czameclti 
and Douglas R. Lord. January 1953. 31p. diagrs., 
photos. (NACA RM L52K28) 



SOME MEASUREMENTS OF FLYTNG QUALITIES OF 
A DOUGLAS D-558-H RESEARCH AIRPLANE DUR- 
ING FLIGHTS TO SUPERSONIC SPEEDS. Herman O. 
Ankenbruck and Theodore E. Dahlen. March 1953. 
25p. diagrs., photos., tab. (NACA RM L53A06) 



LIFT, DRAG, AND HINGE MOMENTS AT SUPER- 
SONIC SPEEDS OF AN ALL-MOVABLE TRIANGULAR 
WTNG AND BODY COMBINATION. William C. Drake. 
September 1953. 38p. diagrs., photos., tabs. 
(NACA RM A53F22) 



A FLIGHT INVESTIGATION AT MACH NUMBERS 
FROM 0.67 TO 1.81 OF THE LONGITUDINAL 
STABILITY AND CONTROL CHARACTERISTICS OF 
A 60° DELTA-WING MISSILE CONFIGURATION 
HAVING AN ALL-MOVABLE TAIL. Martin T. 
Moul and Hal T. Baber, Jr. October 1953. 43p. 
diagrs., photo. (NACA RM L53G29) 



SUBSONIC AND SUPERSONIC HINGE -MOMENT AND 
EFFECTIVENESS CHARACTERISTICS OF AN UN- 
BALANCED LATERAL CONTROL HAVING LOW 
THEORETICAL HINGE MOMENTS AT SUPERSONIC 
SPEEDS. Kennith L. Goin and William E. Palmer. 
October 1953. 55p. diagrs., photos. 
(NACA RM L53G31a) 



171 



(1) AERODYNAMICS 



ROCKET -MODEL INVESTIGATION TO DETERMINE 
THE HINGE-MOMENT AND NORMAL-FORCE 
PROPERTIES OF A FULL-SPAN, CONSTANT- 
CHORD, PARTIALLY BALANCED TRAILING-EDGE 
CONTROL ON A 60° CLIPPED DELTA WING BE- 
TWEEN MACH NUMBERS OF 0.50 AND 1.26. 
C. William Martz and John W. Goslee. October 
1053. 33p. diagrs., photos., tab. 
(NACA RM L53I04) 



LOW-SPEED STATIC STABILITY AND CONTROL 
CHARACTERISTICS OF A 1/4-SCALE MODEL OF 
THE BELL X-I AIRPLANE EQUD7PED WITH A 
4-PERCENT-THICK, ASPECT-RATIO-4, UNSWEPT 
WING. William C. Moseley, Jr., and Robert T. 
Taylor. November 1953. 53p. diagrs., photos., 
tab. (NACA RM L53H27) 



AN INVESTIGATION AT MACH NUMBER 2.40 OF 
FLAP-TYPE CONTROLS EQUIPPED WITH OVER- 
HANG NOSE BALANCES. James N. Mueller. 
November 1953. 95p. diagrs., photos., tab. 
(NACA RM L53I21) 



CONTROL HINGE -MOMENT AND EFFECTD7ENESS 
CHARACTERISTICS OF SEVERAL INTERCHANGE- 
ABLE TIP CONTROLS ON A 60° DELTA WING AT 
MACH NUMBERS OF 1.41, 1.62, AND 1.96. -Odell 
A, Morris. November 1953. 33p. diagrs., photo., 
tab. (NACA RM L53j08a) 



EFFECTS OF LEADING-EDGE CHORD EXTENSIONS 
AND AN ALL-MOVABLE HORIZONTAL TAIL ON 
THE AERODYNAMIC CHARACTERISTICS OF A 
WING-BODY COMBINATION EMPLOYING A TRI- 
ANGULAR WING OF ASPECT RATIO 3 MOUNTED IN 
A HIGH POSITION AT SUBSONIC AND SUPERSONIC 
SPEEDS. Benton E. Wetzel and Frank A- Pfyl. 
January 1954. 35p. diagrs., photo., tabs. 
(NACA RM A53J 14a) 



INVESTIGATION OF A TRAILING-EDGE PADDLE - 
CONTROL SURFACE ON A TRIANGULAR WING OF 
ASPECT RATIO 2 AT SUBSONIC AND SUPERSONIC 
SPEEDS. Louis H. Ball. February 1954. 18p. 
diagrs., tab. (NACA RM A53K20) 



AERODYNAMIC CHARACTERISTICS OF A FULL- 
SPAN TRAILING-EDGE CONTROL ON A 60° DELTA 
WING WITH AND WITHOUT A SPOILER AT MACH 
NUMBER 1.61. Douglas R. Lord and K. R. 
Czarnecki. March 1954. 49p. diagrs., photos., 
tab. (NACA RM L53L17) 



LOW -SPEED CHORDWISE PRESSURE DISTRIBU- 
TIONS NEAR THE MIDSPAN STATION OF THE 
SLOTTED FLAP AND AILERON OF A 1/4-SCALE 
MODEL OF THE BELL X-l AIRPLANE- WITH A 
4-PERCENT-THICK, ASPECT-RATIO-4, UNSWEPT 
WING- William C. Moseley, Jr., and Robert T. 
Taylor. March 1954, 59p. diagrs., photos., tabs. 
(NACA RM L53L18) 



AERODYNAMIC CHARACTERISTICS OF SEVERAL 
TIP CONTROLS ON A 60<> DELTA WING AT A MACH 
NUMBER OF 1.61. Douglas R. Lord and K. R. 
Czarnecki. August 1954. 44p. diagrs., photos., 
tabs. (NACA RM L54E25) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR-ARC SECTIONS AND 40° SWEEPBACK. 
STABILITY AND CONTROL CHARACTERISTICS AT 
A MACH NUMBER OF 1.61 OF THE COMPLETE 
CONFIGURATION EQUIPPED WITH SPOILERS. 
Clyde V. Hamilton and Cornelius Driver. September 
1954. 28p. diagrs. (NACA RM L54F15) 



EFFECTS OF OVERHANG BALANCE ON THE 
HINGE -MOMENT AND EFFECTIVENESS CHARAC- 
TERISTICS OF AN UNSWEPT TRAILING-EDGE 
CONTROL ON A 60° DELTA WING AT TRANSONIC 

AND SUPERSONIC SPEEDS. Lawrence D. Guy. 
September 1954. 48p. diagrs., photo. 
(NACA RML54Gl2a) 



FREE -FLIGHT MEASUREMENTS OF THE ROLLING 
EFFEdTVENESS AND OPERATING CHARACTER- 
ISTICS OF A BELLOWS-ACTUATED SPLIT-FLAP 
AILERON ON A 60° DELTA WING AT MACH NUM- 
BERS BETWEEN 0.8 AND 1.8. Eugene D. Schult. 
October 1954. 33p. diagrs., photos. 
(NACA RM L54H17) 



EFFECTS OF A DETACHED TAB ON THE HINGE- 
MOMENT AND EFFECTIVENESS CHARACTER- 
ISTICS OF AN UNSWEPT TRAILING-EDGE CON- 
TROL ON A 60° DELTA WING AT MACH NUMBERS 
FROM 0.75 TO 1.96. Odell A. Morris and 
Gertrude C. Westrick. April 1955. 36p. diagrs., 
photo. (NACA RM L55B15) 



LOW -SPEED PRESSURE-DISTRIBUTION INVESTI- 
GATION OF A SPOILER AND A SPOILER -SLOT- 
DEFLECTOR ON A 30° SWEPTBACK WING- 
FUSELAGE MODEL HAVING AN ASPECT RATIO 
OF 3, A TAPER RATIO OF 0.5, AND NACA 65A004 
AIRFOIL SECTION. Alexander D. Hammond. 
January 1956. 176p. diagrs., tabs. 
(NACA RM L55I29) 



AERODYNAMIC LOADINGS ASSOCIATED WITH 
SWEPT AND UNSWEPT SPOILERS ON A FLAT 
PLATE AT MACH NUMBERS OF 1.61 AND 2.01. 
Douglas R. Lord and K. R. Czarnecki. March 1956. 
174p. diagrs., photos., tabs. (NACA RM L55L12) 



AERODYNAMIC DAMPING AT MACH NUMBERS OF 
1.3 AND 1.6 OF A CONTROL SURFACE ON A TWO- 
DIMENSIONAL WING BY THE FREE -OSCILLATION 
METHOD. W. J. Tuovila and Robert W. Hess.. 
May 1956. 21p. diagrs., tabs. (NACA RM L 56 A 26a) 



HINGE MOMENT AND EFFECTIVENESS OF AN 
UNSWEPT CONSTANT -CHORD CONTROL AND AN 
OVERHANG-BALANCED, SWEPT HINGE-LINE 
CONTROL ON AN 80° SWEPT POINTED WING AT 
MACH NUMBERS FROM 0.75 TO 1.96. Lawrence D. 
Guy. August 1956. 39p. diagrs., photo. 
(NACARML56F11) 



EXPERIMENTAL HINGE MOMENTS ON FREELY 
OSCILLATING FLAP-TYPE CONTROL SURFACES. 
C. William Martz. October 1956. 29p. diagrs., 
photos., tab. (NACA RM L56G20) 



GROUND EFFECTS ON THE LONGITUDINAL CHAR- 
ACTERISTICS OF TWO MODELS WITH WINGS 
HAVING LOW ASPECT RATIO AND POINTED TD?S. 
Donald A. Buell and Bruce E. Tin ling. July 1957. 
48p. diagrs., photos., tabs. (NACA TN 4044. 
Supersedes RM A55E04) 



AN ANALYTICAL INVESTIGATION OF THE GUST- 
ALLEVIATING PROPERTIES OF A SIMPLE PITCH 
DAMPER. Norman L. Crabill. December 1957. 
47p. diagrs., tab. (NACA TN 4173) 



172 



(1) AERODYNAMICS 



SUBSONIC FLIGHT INVESTIGATION OF METHODS 
TO IMPROVE THE DAMPING OF LATERAL OSCIL- 
LATIONS BY MEANS OF A VISCOUS DAMPER IN 
THE RUDDER SYSTEM IN CONJUNCTION WITH 
ADJUSTED HINGE-MOMENT PARAMETERS. 
Harold L. Crane, George J. Hurt, Jr., and 
John M. Elliott. January 1958. 45p. diagrs., 
photos,, tab. (NACA TN 4193. Supersedes 
RM L54D09) 



SURFACE PRESSURE DISTRIBUTIONS ON A LARGE- 
SCALE 490 SWEPTBACK WTNG-BODY-TAIL CON- 
FIGURATION WITH BLOWING APPLIED OVER THE 
FLAPS AND WING LEADING EDGE. H. Clyde 
McLemore and Marvin P. Fink. February 1958. 
129p. diagrs., photo., tabs. (NACA RM L57K25) 



(1.8.2.6) 
AUTOMATIC 



A PRELIMINARY FLIGHT INVESTIGATION OF THE 
EFFECT OF SNAKING OSCILLATIONS ON THE 
PILOTS' OPINIONS OF THE FLYING QUALITIES OF 
A FIGHTER AIRPLANE. Arnold R. Beckhardt, 
John A. Harper, and William L. AUord. 
September 26, 1950. 31p. diagrs., photos., tabs. 
(NACA RML50E 17a) 



THEORETICAL INVESTIGATION OF THE PER- 
FORMANCE OF PROPORTIONAL NAVIGATION 
GUIDANCE SYSTEMS - EFFECT OF MISSILE CON- 
FIGURATION ON THE SPEED OF RESPONSE. 
Marvin Abramovitz. January 1953. 20p. diagrs., 
tabs. (NACA RM A52J22> 



A THEORETICAL STUDY OF THE EFFECT OF 
CONTROL-DEFLECTION AND CONTROL-RATE 
LIMITATIONS ON THE NORMAL ACCELERATION 
AND ROLL RESPONSE OF A SUPERSONIC INTER- 
CEPTOR. Howard F. Matthews and Stanley F. 
Schmidt. April 1953. 28p. photos., diagrs., 
tabs. (NACA RM A53B11) 



THE INTERPRETATION OF NONLINEAR PITCHING 
MOMENTS IN RELATION TO THE PITCH-UP 
PROBLEM, George S. Campbell and Joseph Weil. 
October 1953. 32p. diagrs., tabs. 
(NACA RM L53I02) 



A THEORETICAL INVESTIGATION OF THE EF- 
FECT OF AUXILIARY DAMPING ON THE LONGI- 
TUDINAL RESPONSE OF A TRANSONIC BOMBER 
CONFIGURATION IN FLIGHT THROUGH CON- 
TINUOUS TURBULENCE. T. F. Bridgland, Jr. 
March 1955. 26p. diagrs., tab. 
(NACA RM L54K15a) 



A THEORETICAL INVESTIGATION OF A COMPEN- 
SATING NETWORK WITH APPLICATION TO ROLL 
CONTROL SYSTEMS FOR AUTOMATIC INTERCEP- 
TORS. Windsor L. Sherman. July 1955. 64p. 
diagrs.. tab. (NACA RM L55E20) 



APPLICATION OF STATISTICAL THEORY TO 
BEAM-RIDER GUIDANCE IN THE PRESENCE OF 
NOISE. I - WIENER FILTER THEORY. Elwood C. 
Stewart. August 1955. 40p. diagrs., tabs. 
(NACARM A55EU) 



SIMULATOR STUDIES OF THE ATTACK PHASE OF 
AN AUTOMATICALLY CONTROLLED INTERCEP- 
TOR. I - PRELIMINARY STUDIES OF THE LATER- 
AL AND LONGITUDINAL CONTROL SYSTEMS. 
Albert A. Schy, Ordway B. Gates, Jr., and C. H. 
Woodling. II - SOME RESULTS OF A STUDY PER- 
FORMED ON THE TYPHOON COMPUTER. Windsor 
L. Sherman and Leonard Sternfield. August 1955. 
24p. diagrs. (NACA RM L55E27a) 



ANALYSIS OF EFFECTS OF AIRPLANE CHARAC- 
TERISTICS AND AUTOPILOT PARAMETERS ON A 
ROLL-COMMAND SYSTEM WTTH AILERON RATE 
AND DEFLECTION LIMITING. Albert A. Schy and 
Ordway B. Gates, Jr. September 1955. 68p. 
diagrs., tab. (NACA RM L55E18) 



A FLIGHT INVESTIGATION OF THE HANDLING 
CHARACTERISTICS OF A FIGHTER AIRPLANE 
CONTROLLED THROUGH AUTOMATIC -PILOT 
CONTROL SYSTEMS. S. A. Sjoberg. September 
1955. 12p. diagrs., tabs. (NACA RM L55F01b) 



ANALYSIS OF A FLIGHT INVESTIGATION AT 
SUPERSONIC SPEEDS OF A SIMPLE HOMING 
SYSTEM. Robert A. Gardiner, Clarence L. Glllis, 
andG. B. Graves, Jr. January 1956. 55p. diagrs., 
photos. (NACA RM L55J28) 



A FLIGHT INVESTIGATION OF THE HANDLING 
CHARACTERISTICS OF A FIGHTER AIRPLANE 
CONTROLLED THROUGH AN ATTITUDE TYPE OF 
AUTOMATIC PILOT. S. A. Sjoberg, Walter R. 
Russell, and William L. Alford. April 1956. 60p. 
diagrs., photos., tabs. (NACA RM L56A12) 



AN EVALUATION OF AN AEROMECHANICAL 
METHOD OF MINIMIZING SERVO-MISSILE 
TRANSFER-FUNCTION VARIATIONS WITH FLIGHT 
CONDITION. Martin L. Nason. April 1956. 41p. 
diagrs., tabs. (NACA RM L56A31) 



EXPERIMENTAL AND PREDICTED LONGITUDINAL 
AND LATERAL-DIRECTIONAL RESPONSE CHAR- 
ACTERISTICS OF A LARGE FLEXIBLE 35° SWEPT - 
WING AIRPLANE AT AN ALTITUDE OF 35,000 FEET. 
Henry A. Cole, Jr., Stuart C. Brown, and Euclid C. 
Holleman. 1957. ii, 39p. diagrs., photo., tabs. 
(NACA Rept. 1330. Supersedes RM A54H09; 
TN 3874) 



ANALYTICAL INVESTIGATION OF ACCELERA- 
TION RESTRICTION IN A FIGHTER AIRPLANE 
WITH AN AUTOMATIC CONTROL SYSTEM. 
James T. Matthews, Jr. January 1958. 24p. 
diagrs. (NACA TN 4179) 



MEASURED AND PREDICTED DYNAMIC RESPONSE 
CHARACTERISTICS OF A FLEXIBLE AIRPLANE TO 
ELEVATOR CONTROL OVER A FREQUENCY RANGE 
INCLUDING THREE STRUCTURAL MODES. 
Henry A. Cole, Jr., and Euclid C. Holleman. 
February 1958. 81p. diagrs., photo., tabs. 
(NACA TN 4147) 



APPLICATION OF STATISTICAL THEORY TO 
BEAM-RIDER GUIDANCE IN THE PRESENCE OF 
NOISE. H - MODIFIED WIENER FILTER THEORY. 
Elwood C. Stewart. June 1958. (1), 48p. diagrs;; 
tabs. (NACA TN 4278, Supersedes RM A55Ella) 



173 



(1) AERODYNAMICS 



(1.8.2. 7) 
JET REACTION 



INTERNAL CHARACTERISTICS AND PERFORM- 
ANCE OF SEVERAL JET DEFLECTORS AT 
PRIMARY-NOZZLE PRESSURE RATIOS UP TO 
3.0. Jack G. McArdle. June 1958. ii, 107p. 
diagrs., photos., tabs. (NACA TN 4264) 



INTERNAL CHARACTERISTICS AND PERFORM- 
ANCE OF AN AERODYNAMICALLY CONTROLLED, 
VARIABLE -DISCHARGE CONVERGENT NOZZLE. 
Jack G. McArdle. July 1958. 33p. diagrs., photo., 
tabs. (NACA TN 4312) 



EXPERIMENTAL INVESTIGATION OF AXIAl. AND 
NORMAL FORCE CHARACTERISTICS OF SKEWED 
NOZZLES. David J. Carter, Jr., and Allen R. 
Vick. September 1958. 40p. diagrs., photos. 
(NACA TN 4336) 



(1.8.3) 
SPINNING 



AN INVESTIGATION IN THE LANGLEY 20-FOOT 
FREE -SPINNING TUNNEL OF THE SPIN AND RE- 
COVERY CHARACTERISTICS OF A l/30-SCALE 
MODEL OF THE BELL X-2 AIRPLANE. Lawrence 
J. Gale. July 20, 1949. 15p. diagrs., photo., tabs. 
(NACA RM L9G15a) 



SUMMARY OF SPIN AND RECOVERY CHARACTER- 
ISTICS OF 12 MODELS OF FLYING- WING AND 
UNCONVENTIONAL-TYPE AIRPLANES. Ralph W. 
Stone, Jr., and Burton E. Hultz. March 1, 1951. 
95p. diagrs., photo., tabs. (NACA RM L50L29) 



FREE-SPINNING TUNNEL INVESTIGATION OF A 
1/20-SCALE MODEL OF THE DOUGLAS X-3 AIR- 
PLANE. Burton E. Hultz. December 26, 1951. 
23p. diagrs., photos., tab. (NACA RM L51K12) 



FREE-SPINNING-TUNNEL INVESTIGATION TO DE- 
TERMINE THE EFFECT OF SPINS AND RECOVER- 
IES OF WTNG LEADING-EDGE CHORD-EXTENSIONS 
AND DROOPED LEADING-EDGE FLAPS ON SCALE 
MODELS OF TWO SWEPTBACK-WING FIGHTER 
AIRPLANES. Jack H. Wilson and Walter J. Klinar. 
May 1953. 28p. photo., diagrs., tabs. 
(NACA RM L53C06) 



COMPARISON OF EFFECTS OF AILERONS AND 
COMBINATIONS OF SPOILER-SLOT-DEFLECTOR 
ARRANGEMENTS ON SPIN RECOVERY OF SWEPT- 
BACK-WING MODEL HAVING MASS DISTRIBUTED 
ALONG THE FUSELAGE. Frederick M, Healy and 
Walter J. Klinar. November 1954. 18p. diagrs., 
photo., tabs. (NACA RM L54I14) 



SPINNING AND RELATED PROBLEMS AT HIGH 
ANGLES OF ATTACK FOR HIGH-SPEED AIR- 
PLANES. Walter J. Klinar. March 1956. 8p. 
diagrs. (NACA RM L55L23a) 



STATUS OF SPIN RESEARCH FOR RECENT AIR- 
PLANE DESIGNS. Anshal I. Neihouse, Salter J. 
Klinar, and Stanley H. Scher. August 1957. ii, 
98p. diagrs., photos., tabs. (NACA RM L5.7F12) 



EFFECT OF FLOW INCIDENCE AND REYNOLDS 
NUMBER ON LOW-SPEED AERODYNAMIC CHAR- 
ACTERISTICS OF SEVERAL NONCIRCULAR CYL- 
INDERS WITH APPLICATIONS TO DIRECTIONAL 
STABILITY AND SPINNING. Edward C Polhamus. 
January 1958. 54p. diagrs., photo., tab. 
(NACA TN 4176) 



(1.8.4) 
STALLING 



LONGITUDINAL STABILITY AND CONTROL CHAR- 
ACTERISTICS OF AN AIRPLANE MODEL HAVING A 
42.8° SWEPTBACK CIRCULAR- ARC WTNG WITH 
ASPECT RATIO 4.00, TAPER RATIO 0.50, AND 
SWEPTBACK TAIL SURFACES. Joseph Weil, Paul 
Comisarow, and Kenneth W. Good son. October 17, 
1947. 84p. diagrs., photos., tab. 
(NACA RM L7G28) 



AN INVESTIGATION OF THE LONGITUDINAL CHAR- 
ACTERISTICS OF THE X-3 CONFIGURATION WITH 
WING AND HORIZONTAL TAIL SURFACES OF 
ASPECT RATIO 3.0 BY MEANS OF ROCKET- 
PROPE LLED MODELS . RESULTS AT HIGH LIFT 
COEFFICIENTS. Robert F. Peck and Jesse L. 
Mitchell. August 27, 1951. 34p. diagrs., photos. 
(NACA RM L51G10) 



LONGITUDINAL AERODYNAMIC CHARACTERISTICS 
OF MODEL AIRPLANE CONFIGURATION EQUIPPED 
WITH A SCALED X-l AIRPLANE WING. James H. 
Parks. April 1952. 37p. diagrs. 
(NACA RM L51L10a) 



CORRELATION OF FLIGHT AND WIND-TUNNEL 
MEASUREMENTS OF ROLL-OFF IN LOW-SPEED 
STALLS ON A 35° SWEPT -WING AIRCRAFT, Seth 
B. Anderson. September 1953. 17p. diagrs., 
photos., tabs. (NACA RM A53G22) 



STABILITY AND CONTROL CHARACTERISTICS 
OBTAINED DURING DEMONSTRATION OF THE 
DOUGLAS X-3 RESEARCH AIRPLANE. Richard E. 
Day and Jack Fischel. July 1955. 51p. diagrs., 
photos., tab. (NACA RM H55E16) 



EFFECT OF SEVERAL WING MODIFICATIONS ON 
THE LOW-SPEED STALLING CHARACTERISTICS OF 
THE DOUGLAS D-558-H RESEARCH AIRPLANE. 
Jack Fischel and Donald Reisert. July 1955. 62p. 
diagrs., photos., tabs. (NACA RM H55E31a) 



LARGE-SCALE WIND-TUNNEL TESTS OF AN AIR- 
PLANE MODEL WITH A 450 SWEPTBACK WING OF 
ASPECT RATIO 2.8 WITH AREA SUCTION APPLIED 
TO TRAILING-EDGE FLAPS AND WITH SEVERAL 
WING LEADING-EDGE MODIFICATIONS. David G. 
Koenig and Kiyoshi Aoyagi. November 1956. 66p. 
diagrs., photo., tabs. (NACA RM A56H08) 



174 



(1) AERODYNAMICS 



A SUMMARY AND ANALYSIS OF THE LOW -SPEED 
LONGITUDINAL CHARACTERISTICS OF SWEPT 
WINGS AT HIGH REYNOLDS NUMBER. G. Chester 
Furlong and James G. McHugh. 1957. iii, 149p. 
diagrs., tabs. (NACA Rept. 1339. Supersedes 
RM L52D16) 



FLIGHT INVESTIGATION OF THE LOW-SPEED 
CHARACTERISTICS OF A 35© SWEPT -WING AIR- 
PLANE EQUIPPED WITH AN AREA-SUCTION 
EJECTOR FLAP AND VARIOUS WING LEADING- 
EDGE DEVICES. Seth B. Anderson, Alan E. Faye, 
Jr., and Robert C. Innis. September 1957. 28p. 
diagrs., photos., tab. (NACA RM A57G10) 



THE USE OF A LEADING-EDGE AREA-SUCTION 
FLAP AND LEADING-EDGE MODIFICATIONS TO 
IMPROVE THE HIGH-LIFT CHARACTERISTICS OF 
AN AIRPLANE MODEL WITH A WING OF 45° 
SWEEP AND ASPECT RATIO 2.8. David G. Koenig 
andKiyoshi Aoyagl. November 1957. 46p. diagrs., 
photo., tabs. (NACA RM A57H21) 



WIND-TUNNEL INVESTIGATION OF THE USE OF 
LEADING-EDGE AND TRAILING-EDGE AREA- 
SUCTION FLAPS ON A 13-PERCENT -THICK 
STRAIGHT WING AND FUSELAGE MODEL. Curt A. 
Holzhauser. January 1958. 26p. diagrs., photo., 
tabs. (NACA RM A57K01) 



DATA FROM FLOW -FIELD SURVEYS BEHIND A 
LARGE-SCALE THIN STRAIGHT WING OF ASPECT 
RATIO 3, William T. Evans. June 1958. 13p. 
diagrs. (NACA RM A58D17) 



(1.8.5) 
FLYING QUALITIES 



RESULTS OBTAINED DURING EXTENSION OF U.S. 
AIR FORCE TRANSONIC-FLIGHT TESTS OF XS-1 
AIRPLANE. Harold R. Goodman and Hubert M. 
Drake. November 16, 1948. 12p. diagrs. 
(NACA RM L8I28) 



ESTIMATED TRANSONIC FLYING QUALITIES OF A 
TAILLESS AIRPLANE BASED ON A MODEL INVES- 
TIGATION. Charles J. Donlan and Richard E. Kuhn. 
June 8, 1949. 63p. diagrs. t photos., tabs. 
(NACA RM L9D08) 



FLIGHT TESTS OF A MODEL HAVING SELF- 
SUPPORTING FUEL-CARRYING PANELS HINGED 
TO THE WING TD?S. Robert E. Shanks and David C. 
Gran a. November 2, 1949. lOp. diagrs., tab. 
(NACA RM L9I07a) 



INVESTIGATION OF THE DYNAMIC LATERAL 
STABIJJTY AND CONTROL CHARACTERISTICS OF 
A MODEL OF A FIGHTER AIRPLANE WITHOUT A 
HORIZONTAL TATL AND EQUIPPED WITH EITHER 
SINGLE OR TWIN VERTICAL TAILS. John W. 
Draper and Robert W. Rose. November 15, 1949. 
20p. diagrs., photos., tab. (NACA RM L9J07a) 



A PRELIMINARY FLIGHT INVESTIGATION OF THE 
EFFECT OF SNAKING OSCILLATIONS ON THE 
PILOTS' OPINIONS OF THE FLYING QUALITIES OF 
A FIGHTER AIRPLANE. Arnold R. Beckhardt, 
John A. Harper, and William L. Alford. 
September 26, 1950. 31p. diagrs., photos., tabs. 
(NACA RM L50E 17a) 



FREE -FLIGHT -TUNNEL INVESTIGATION OF THE 
DYNAMIC LATERAL STABILITY AND CONTROL 
CHARACTERISTICS OF A HIGH-ASPECT -RATIO 
BOMBER MODEL WITH SELF-SUPPORTING FREE- 
FLOATING FUEL TANKS ATTACHED TO THE WING 
TIPS. Charles V. Bennett and Robert B. Cadman. 
August 1951. 12p. diagrs., tab. (NACA RM L51E17) 



HANDLING QUALITIES OF HIGH-SPEED AIRPLANES. 

W. C. Williams and A. S. Crossfield. January 1952. 
17p. diagrs. (NACA RM L52A08) 



THE STATIC AND DYNAMIC LONGITUDINAL STA- 
BILITY CHARACTERISTICS OF SOME SUPERSONIC 
AIRCRAFT CONFIGURATIONS. Jesse L. Mitchell. 
January 1952. 19p. diagrs. (NACA RM L52A10a) 



FREE-FLIGHT -TUNNEL INVESTIGATION OF THE 
DYNAMIC LATERAL STABILITY AND CONTROL 
CHARACTERISTICS OF A HIGH- ASPECT -RATIO 
BOMBER MODEL WITH A SWEPT BACK -WING 
FIGHTER MODEL ATTACHED TO EACH WING TIP. 
Charles V. Bennett and Peter C. Boisseau. 
September 1952. 17p. diagrs., tabs. 
(NACA RM L52E08) 



SOME MEASUREMENTS OF FLYING QUALITIES OF 
A DOUGLAS D-558-II RESEARCH AfflPLANE DUR- 
ING FLIGHTS TO SUPERSONIC SPEEDS. Herman O. 
Ankenbruck and Theodore E. Dahlen. March 1953. 
25p. diagrs., photos., tab. (NACA RM L53A06) 



SOME MEASUREMENTS OF THE BUFFET REGION 
OF A SWEPT-WING RESEARCH AIRPLANE DURING 
FLIGHTS TO SUPERSONIC MACH NUMBERS. 
Thomas F. Baker. May 1953. 14p. diagrs., 
photos., tab. (NACA RM L53D06) 



MEASUREMENTS OBTAINED DURING THE GLIDE- 
FLIGHT PROGRAM OF THE BELL X-2 RESEARCH 
AmPLANE. Richard E. Day. July 30, 1953. 27p. 
diagrs., photos., tabs. (NACA RM L53G03a) 



CORRELATION OF FLIGHT AND WIND-TUNNEL 
MEASUREMENTS OF ROLL-OFF IN LOW-SPEED 
STALLS ON A 35° SWEPT-WING AIRCRAFT. Seth 
B. Anderson. September 1953. 17p. diagrs., 
photos., tabs. (NACA RM A53G22) 



SOME MEASUREMENTS OF BUFFETING ENCOUN- 
TERED BY A DOUGLAS D-558-II RESEARCH AIR- 
PLANE IN THE MACH NUMBER RANGE FROM 0.5 
TO 0.95. Thomas F. Baker. November 1953, 22p. 
diagrs., photos., tabs. (NACA RM L53I17) 



DETERMINATION OF LONGITUDINAL STABILITY 
IN SUPERSONIC ACCELERATED MANEUVERS FOR 
THE DOUGLAS D-558-H RESEARCH AIRPLANE. 
Herman O. Ankenbruck. February 1954. 29p. 
diagrs., photos., tab. (NACA RM L53J20) 



MEASURED DATA PERTAINING TO BUFFETING AT 
SUPERSONIC SPEEDS OF THE DOUGLAS D-558-II 
RESEARCH AIRPLANE. Thomas F. Baker. 
February 1954. 16p. diagrs., photos., tab. 
(NACA RM L53L10) 



175 



( 1 ) AERODYNAMICS 



LONGITUDINAL STABILITY CHARACTERISTICS IN 
ACCELERATED MANEUVERS AT SUBSONIC AND 
TRANSONIC SPEEDS OF THE DOUGLAS D-558-II 
RESEARCH AIRPLANE EQUIPPED WITH A 
LEADING-EDGE WING CHORD-EXTENSION. Jack 
Fischel and Cyril D. Brunn. October 1954. 62p. 
diagrs., photos., tab. (NACA RM H54H16) 



AN INVESTIGATION OF A SUPERSONIC AIRCRAFT 
CONFIGURATION HAVING A TAPERED WING WITH 
CIRCULAR- ARC SECTIONS AND 40° SWEEPBACK. 
STATIC LONGITUDINAL AND LATERAL STABILITY 
AND CONTROL CHARACTERISTICS AT A MACH 
NUMBER OF 1.89. M. Leroy Spearman and Edward 
B. Palazzo. October 1954. 24p. diagrs., photo., 
tab. (NACA RM L54G26a) 



ANALYTICAL STUDY OF THE EFFECT OF 
CENTER-OF-GRAVITY POSITION ON THE RE- 
SPONSE TO LONGITUDINAL CONTROL IN LANDING 
APPROACHES OF A SWEPT -WING AIRPLANE OF 
LOW ASPECT RATIO HAVING NO HORIZONTAL 
TAIL. Ralph W. Stone, Jr. October 1954. 35p. 
diagrs., tabs. (NACA RM L54H04) 



DETERMINATION OF LONGITUDINAL HANDLING 
QUALITIES OF THE D-558-II RESEARCH AIRPLANE 
AT TRANSONIC AND SUPERSONIC SPEEDS TO A 
MACH NUMBER OF ABOUT 2.0. Herman O. 
Ankenbruck. November 1954. 25p. diagrs., photos., 
tab. (NACA RM H54G29a) 



LATERAL MOTIONS ENCOUNTERED WITH THE 
DOUGLAS D-558-II ALL-ROCKET RESEARCH AIR- 
PLANE DURING EXPLORATORY FLIGHTS TO A 
MACH NUMBER OF 2.0. Herman O. Ankenbruck 
and Chester H. Wolowicz. December 1954. 32p. 
diagrs., photos., tab. (NACA RM H54I27) 



RESULTS OF MEASUREMENTS MADE DURING 
THE APPROACH AND LANDING OF SEVEN HIGH- 
SPEED RESEARCH AIRPLANES. Wendell H. 
Stillwell. February 1955. 25p. diagrs., tab. 
(NACA RM H54K24) 



FLIGHT EXPERIENCE WITH TWO HIGH-SPEED 
AIRPLANES HAVING VIOLENT LATERAL- 
LONGITUDINAL COUPLING IN AILERON ROLLS. 
NACA High-Speed Flight Station. February 1955. 
30p. diagrs., photos., tabs. (NACA RM H55A13) 



LATERAL STABILITY AND CONTROL CHARACTER- 
ISTICS OF THE CONVAIR XF-92A DELTA-WING 
AIRPLANE AS MEASURED IN FLIGHT. Thomas R. 
Sisk and Duane O. Muhleman. May 1955. 55p, 
diagrs., photos., tabs. (NACA RM H55A17) 



STABILITY AND CONTROL CHARACTERISTICS 
OBTAINED DURING DEMONSTRATION OF THE 
DOUGLAS X-3 RESEARCH AIRPLANE. Richard E. 
Day and Jack Fischel. July 1955. 51p. diagrs., 
photos., tab. (NACA RM H55E16) 



A FLIGHT INVESTIGATION OF THE HANDLING 
CHARACTERISTICS OF A FIGHTER AIRPLANE 
CONTROLLED THROUGH AUTOMATIC-PILOT 
CONTROL SYSTEMS. S. A. Sjoberg. September 
1955. 12p. diagrs., tabs. (NACA RM L55F01b) 



FLIGHT MEASUREMENTS OF DIRECTIONAL STA- 
BILITY TO A MACH NUMBER OF 1.48 FOR AN 
AIRPLANE TESTED WITH THREE DIFFERENT 
VERTICAL TAIL CONFIGURATIONS. Hubert M. 
Drake, Thomas W., Finch, and James R. Peele. 
October 1955. 22p. diagrs., photos., tab. 
(NACA RM H55G26) 



SOME RECENT RESEARCH ON THE HANDLING 
QUALITIES OF AIRPLANES. Walter C. Williams 
and William H. Phillips. February 1956. 19p. 
diagrs. (NACA RM H55L29a) 



A FLIGHT INVESTIGATION OF THE HANDLING 
CHARACTERISTICS OF A FIGHTER AIRPLANE 
CONTROLLED THROUGH AN ATTITUDE TYPE OF 
AUTOMATIC PILOT. S. A. Sjoberg, Walter R. 
Russell, and William L. Alford. April 1956. 60p. 
diagrs., photos., tabs. (NACA RM L56A12) 



EFFECT OF SEVERAL WING MODIFICATIONS ON 
THE SUBSONIC AND TRANSONIC LONGITUDINAL 
HANDLING QUALITIES OF THE DOUGLAS D-558-U 
RESEARCH AIRPLANE . Jack Fischel and Donald 
Reisert. June 1956. 57p. diagrs., photos., tabs 
(NACA RM H56C30) 



EFFECT OF WING HEIGHT AND DIHEDRAL ON THE 
LAiERAL STABILITY CKARACT ERISTICS AT LOW 
LIFT OF A 45° SWEPT -WING AIRPLANE CONFIG- 
URATION AS OBTAINED FROM TIME-VECTOR 
ANALYSES OF ROCKET -PROPELLED-MODEL 
FLIGHTS AT MACH NUMBERS FROM 0.7 TO 1.3. 
Clarence L. Gillis and Rowe Chapman, Jr. 
September 1956. 70p. diagrs., photos., tabs. 
(NACA RML56E17) 



REVIEW AND INVESTIGATION OF UNSATISFACTO- 
RY CONTROL CHARACTERISTICS INVOLVING IN- 
STABILITY OF PILOT-AIRPLANE COMBINATION 
AND METHODS FOR PREDICTING THESE DIFFI- 
CULTIES FROM GROUND TESTS. William H. 
Phillips, B. Porter Brown, and James T. Matthews, 
Jr. August 1957. 57p. diagrs. (NACA TN 4064. 
Supersedes RM L53F17a) 



FLIGHT -TEST INVESTIGATION ON THE LANGLEY 
CONTROL-LINE FACILITY OF A MODEL OF A 
PROPELLER-DRIVEN TAIL-SITTER-TYPE 
VERTICAL-TAKE-OFF AIRPLANE WITH DELTA 
WING DURING RAPID TRANSITIONS . Robert O . 
Schade. August 1957. 19p. diagrs., photo., tab. 
(NACA TN 4070) 



FLIGHT INVESTIGATION OF THE LOW-SPEED 
CHARACTERISTICS OF A 350 SWEPT -WING AIR- 
PLANE EQUD7PED WITH AN AREA-SUCTION 
EJECTOR FLAP AND VARIOUS WING LEADING- 
EDGE DEVICES. Seth B. Anderson, Alan E. Faye, 
Jr., and Robert C. Innis. September 1957. 28p. 
diagrs., photos., tab. (NACA RM A57G10) 



EFFECT OF GROUND PROXIMITY ON THE AERO- 
DYNAMIC CHARACTERISTICS OF A FOUR-ENGINE 
VERTICAL-TAKE-OFF-AND-LANDING 
TRANSPORT-AIRPLANE MODEL WITH TILTING 
WING AND PROPELLERS. William A. Newsom, 
Jr. October 1957. 15p. diagrs., photo., tab. 
(NACA TN 4124) 



3 76 



(1) AERODYNAMICS 



FLIGHT INVESTIGATION OF THE TRANSONIC 
LONGITUDINAL AND LATERAL HANDLING QUAL- 
ITIES OF THE DOUGLAS X-3 RESEARCH AIRPLANE. 
Jack Fischel, Euclid C. Holleman, and Robert A. 
Tremant. December 1957. 61p. diagrs., photos., 
tab. (NACA RM H57I05) 



TRANSITION-FLIGHT INVESTIGATION OF A 
FOUR-ENGINE-TRANSPORT VERTICAL-TAKE- 
OFF AIRPLANE MODEL UTILIZING A LARGE 
FLAP AND EXTENSIBLE VANES FOR REDIRECT- 
ING THE PROPELLER SLIPSTREAM. Louis P. 
Tosti. December 1957. 35p. diagrs., photos., 
tab., film suppl. available on request. 
(NACA TN 4131) 



SUBSONIC FLIGHT INVESTIGATION OF METHODS 
TO IMPROVE THE DAMPING OF LATERAL OSCIL- 
LATIONS BY MEANS OF A VISCOUS DAMPER IN 
THE RUDDER SYSTEM IN CONJUNCTION WITH 
ADJUSTED HINGE-MOMENT PARAMETERS. 
Harold L. Crane, George J. Hurt, Jr., and 
John M. Elliott. January 1958. 45p. diagrs., 
photos., tab. (NACA TN 4193. Supersedes 
RM L54P09) 



A FLIGHT INVESTIGATION OF THE EFFECTS OF 
VARIED LATERAL DAMPING ON THE EFFEC- 
TIVENESS OF A FIGHTER AIRPLANE AS A GUN 
PLATFORM. Helmut A. Kuehnel, Arnold R. 
Beckhardt, and Robert A. Champine. January 
1958. 30p. diagrs., photo., tabs. (NACA TN 4199. 
Supersedes RM L53F08a) 



(1.8.6) 

MASS AND GYROSCOPIC 

PROBLEMS 



WIND-TUNNEL INVESTIGATION OF THE STABILITY 
OF THE JETTISONABLE NOSE SECTION OF THE 
XS-2 AIRPLANE. Stanley H. Scher and Roscoe H. 
Goodwin. October 14, 1948. 19p. diagrs., photos., 
tabs. (NACA RM L8I14) 



AN INVESTIGATION IN THE LANGLEY 20-FOOT 
FREE -SPINNING TUNNEL OF THE SPIN AND RE- 
COVERY CHARACTERISTICS OF A 1/30-SCALE 
MODEL OF THE BELL X-2 AIRPLANE. Lawrence 
J. Gale. July 20, 1949. 15p. diagrs., photo., tabs. 
(NACA RM L9G15a) 



SUMMARY OF SPIN AND RECOVERY CHARACTER- 
ISTICS OF 12 MODELS OF FLYING -WING AND 
UNCONVENTIONAL-TYPE AIRPLANES.- Ralph W. 
Stone, Jr., andBurtonE. Hultz. March 1, 1951. 
95p. diagrs., photo., tabs. (NACA RM L50L29) 



FREE-SPINNING TUNNEL INVESTIGATION OF A 
1/20 -SCALE MODEL OF THE DOUGLAS X-3 AIR- 
PLANE. Burton E. Hultz. December 26, 1951. 
23p. diagrs., photos., tab. (NACA RM L51K12) 



EXPLORATORY ROCKET FLIGHT TESTS TO IN- 
VESTIGATE THE USE OF A FREELY SPINNING 
MONOPLANE TAIL FOR STABILIZING A BODY. 
Paul E. Purser and Joseph E. Stevens. October 
1952. 25p. diagrs., photos., tab. 
(NACA RM L5205a) 



FREE-SPINNING-TUNNEL INVESTIGATION TO DE- 
TERMINE THE EFFECT OF SPINS AND RECOVER- 
IES OF WING LEADING-EDGE CHORD-EXTENSIONS 
AND DROOPED LEADING-EDGE FLAPS ON SCALE 
MODELS OF TWO SWEPTBACK-WING FIGHTER 
AIRPLANES. Jack H. Wilson and Walter J. Klinar. 
May 1953. 28p. photo., diagrs., tabs. 
(NACA RM L53C06) 



COMPARISON OF EFFECTS OF AILERONS AND 
COMBINATIONS OF SPOILER-SLOT-DEFLECTOR 
ARRANGEMENTS ON SPIN RECOVERY OF SWEPT- 
BACK-WING MODEL HAVING MASS DISTRIBUTED 
ALONG THE FUSELAGE. Frederick M. Healy and 
Walter J. Klinar. November 1954. 18p. diagrs., 
photo., tabs. (NACA RM L54I14) 



FLIGHT EXPERIENCE WITH TWO HIGH-SPEED 
AIRPLANES HAVING VIOLENT LATERAL- 
LONGITUDINAL COUPLING IN AILERON ROLLS. 
NACA High-Speed Flight Station. February 1955, 
30p. diagrs., photos., tabs. (NACA RM H55A13) 



EFFECT OF AUTOMATIC STABILIZATION ON THE 
SHDESLIP AND ANGLE -OF -ATTACK DISTURBANCES 
IN ROLLING MANEUVERS. Ordway B. Gates, Jr., 
Joseph Weil, andC. H. Woodling. July 1955. 18p. 
diagrs. (NACA RM L55E25b) 



SIMULATOR STUDIES OF THE ATTACK PHASE OF 
AN AUTOMATICALLY CONTROLLED INTERCEP- 
TOR. I - PRELIMINARY STUDIES OF THE LATER- 
AL AND LONGITUDINAL CONTROL SYSTEMS. 
Albert A. Schy, Ordway B. Gates, Jr., and C. H. 
Woodling. II - SOME RESULTS OF A STUDY PER- 
FORMED ON THE TYPHOON COMPUTER. Windsor 
L. Sherman and Leonard Sternfield. August 1955. 
24p. diagrs. (NACA RM L55E27a) 



SPINNING AND RELATED PROBLEMS AT HIGH 
ANGLES OF ATTACK FOR HIGH-SPEED AIR- 
PLANES. Walter J. Klinar. March 1956. 8p. 
diagrs. (NACA RM L55L23a) 



AN ANALOG STUDY OF THE RELATIVE IMPOR- 
TANCE OF VARIOUS FACTORS AFFECTING ROLL 
COUPLING . Joseph Weil and Richard E . Day . 
April 1956. 81p. diagrs., photo., tabs. 
(NACA RM H56A06) 



ANALYSIS OF AN AUTOMATIC CONTROL TO PRE- 
VENT ROLLING DIVERGENCE. William H. 
Phillips. April. 1956. 31p. diagrs., tab. 
(NACA RM L56A04) 



LATERAL STABILITY CHARACTERISTICS BE- 
TWEEN MACH NUMBERS OF 0.80 AND 1.57 AND 
SIMULATION OF COUPLED MOTION AT MACH 
NUMBER 1.30 OF A ROCKET-PROPELLED MODEL 
OF AN AIRPLANE CONFIGURATION HAVING THIN 
HIGHLY TAPERED 45° SWEPTBACK SURFACES. 
Charles T. D'Aiutolo and Allen B. Henning. April 
1956. 41p. diagrs., photos., tabs. 
(NACA RM L56A17) 



SOME NOTES ON THE VIOLENT LATERAL - 
LONGITUDINAL COUPLING MOTIONS OF THE 
DOUGLAS X-3 AIRPLANE IN AILERON ROLLS. 
Ralph W. Stone, Jr. May 1956. 35p. diagrs., tab. 
(NACA RM L56C15) 



(1) AERODYNAMICS 



177 



AN ANALOG COMPUTER STUDY OF SEVERAL STA- 
BILITY AUGMENTATION SCHEMES DESIGNED TO 
ALLEVIATE ROLL-INDUCED INSTABILITY. Brent 
Y. Creer. February 1957. 50p. diagrs., tab. 
(NACA RM A56H30) 



STATUS OF SPIN RESEARCH FOR RECENT AIR- 
PLANE DESIGNS. Anshal I. Neihouse, Salter J. 
Klinar, and Stanley H. Scher. August 1957. ii, 
98p. diagrs., photos., tabs. (NACA RM L57F12) 



A SIMPLIFIED METHOD FOR APPROXIMATING 
THE TRANSIENT MOTION IN ANGLES OF ATTACK 
AND SIDESLIP DURING A CONSTANT ROLLING 
MANEUVER. Leonard Sternfleld. 1958. ii, lip. 
diagrs., tabs. (NACA Rept. 1344. Supersedes 
RM L56F04) 



A THEORETICAL ANALYSIS OF THE EFFECT OF 
ENGINE ANGULAR MOMENTUM ON LONGITUDINAL 
AND DIRECTIONAL STABILITY IN STEADY ROLL- 
ING MANEUVERS. Ordway B. Gates, Jr., and 
C. H. Woodling. April 1958. 20p. diagrs., tab. 
(NACA TN 4249. Supersedes RM L55G05) 



APPROXIMATE METHOD FOR CALCULATING 
MOTIONS IN ANGLES OF ATTACK AND SIDESLIP 
DUE TO STEP PITCHING- AND YAWING-MOMENT 
INPUTS DURING STEADY ROLL. Martin T. Moul 
and Teresa R. Brennan. September 1958. 42p. 
diagrs., tabs. (NACA TN 4346) 



(1.8.8) 
AUTOMATIC STABILIZATION 



THE EFFECT OF VARIOUS MISSILE CHARACTER- 
ISTICS ON AIRFRAME FREQUENCY RESPONSE. 
Howard F. Matthews and Walter E. McNeill. 
January 1952. 16p. diagrs. /NACA RM A51L17a) 



THEORETICAL INVESTIGATION OF THE PER- 
FORMANCE OF PROPORTIONAL NAVIGATION 
GUIDANCE SYSTEMS - EFFECT OF MISSILE CON- 
FIGURATION ON THE SPEED OF RESPONSE. 
Marvin Abramovitz. January 1953. 20p. diagrs., 
tabs. (NACA RM A52J22) 



A THEORETICAL STUDY OF THE EFFECT OF 
CONTROL-DEFLECTION AND CONTROL-RATE 
LIMITATIONS ON THE NORMAL ACCELERATION 
AND ROLL RESPONSE OF A SUPERSONIC INTER- 
CEPTOR. Howard F. Matthews and Stanley F. 
Schmidt. April 1953. 28p. photos., diagrs., 
tabs. (NACARM A53B11) 



A STUDY OF VISUAL INTERCEPTION ATTACKS 
ON A NONMANEUVERING AIRPLANE TARGET. 
Donald C. Cheatham, Charles W. Mathews, and 
John A. Harper. July 1953. 97p. diagrs., photos., 
tabs. (NACA RM L53E01) 



THE INTERPRETATION OF NONLINEAR PITCHING 
MOMENTS IN RELATION TO THE PITCH -UP 
PROBLEM. George S. Campbell and Joseph Weil. 
October 1953. 32p. diagrs., tabs. 
(NACA RM L53I02) 



A THEORETICAL INVESTIGATION OF THE EF- 
FECT OF AUXILIARY DAMPING ON THE LONGI- 
TUDINAL RESPONSE OF A TRANSONIC BOMBER 
CONFIGURATION IN FLIGHT THROUGH CON- 
TINUOUS TURBULENCE. T. F. Bridgland, Jr. 
March 1955. 26p. diagrs., tab. 
(NACA RML54K15a) 



A THEORETICAL INVESTIGATION OF A COMPEN- 
SATING NETWORK WITH APPLICATION TO ROLL 
CONTROL SYSTEMS FOR AUTOMATIC INTERCEP- 
TORS. Windsor L. Sherman. July 1955. 64p. 
diagrs., tab. (NACA RM L55E20) 



EFFECT OF AUTOMATIC STABILIZATION ON THE 
SIDESLD? AND ANGLE-OF -ATTACK DISTURBANCES 
IN ROLLING MANEUVERS. Ordway B. Gates, Jr., 
Joseph Well, and C. H. Woodling. July 1955. Up. 
diagrs. (NACA RM L55E25b) 



APPLICATION OF STATISTICAL THEORY TO 
BEAM-RIDER GUIDANCE IN THE PRESENCE OF 
NOISE . I - WIENER FILTER THEORY. Elwood C . 
Stewart. August 1955. 40p. diagrs., tabs. 
(NACARMA55EU) 



ANALYSIS OF EFFECTS OF AIRPLANE CHARAC- 
TERISTICS AND AUTOPILOT PARAMETERS ON A 
ROLL-COMMAND SYSTEM WITH AILERON RATE 
AND DEFLECTION LIMITING. Albert A. Schy and 
Ordway B. Gates, Jr. September 1955. 68p. 
diagrs., tab. (NACA RM L55E18) 



A FLIGHT INVESTIGATION OF THE HANDLING 
CHARACTERISTICS OF A FIGHTER AIRPLANE 
CONTROLLED THROUGH AUTOMATIC-PILOT. 
CONTROL SYSTEMS. S. A. Sjoberg. September 
1955. 12p. diagrs., tabs. (NACA RM L55F01b) 



A THEORETICAL ANALYSIS OF A SIMPLE AERO- 
DYNAMIC DEVICE TO IMPROVE THE LONGITUDI- 
NAL DAMPING OF A CRUCIFORM MISSILE CON- 
FIGURATION AT SUPERSONIC SPEEDS. James E. 
Clements. October 1955. 36p. diagrs., tab. 
(NACA RM L55H31) 



ANALYSIS OF A FLIGHT INVESTIGATION AT 
SUPERSONIC SPEEDS OF A SIMPLE HOMING 
SYSTEM. Robert A. Gardiner, Clarence L. Gillis, 
andG. B. Graves, Jr. January 1956. 55p. diagrs., 
photos. (NACA RM L55J28) 



AN ANALOG STUDY OF THE RELATIVE IMPOR- 
TANCE OF VARIOUS FACTORS AFFECTING ROLL 
COUPLING . Joseph Weil and Richard E . Day . 
April 1956. 81p. diagrs., photo., tabs. 
(NACA RM H56A06) 



ANALYSIS OF AN AUTOMATIC CONTROL TO PRE- 
VENT ROLLING DIVERGENCE . William H. 
Phillips. April 1956. 31p. diagrs., tab. 
(NACA RM L56A04) 



A FLIGHT INVESTIGATION OF THE HANDLING 
CHARACTERISTICS OF A FIGHTER AIRPLANE 
CONTROLLED THROUGH AN ATTITUDE TYPE OF 
AUTOMATIC PILOT. S. A. Sjoberg, Walter R. 
Russell, and William L. A If or d. April 1956. 60p. 
diagrs., photos., tabs. (NACA RM L58A12) 



178 



(1) AERODYNAMICS 



AN EVALUATION OF AN AEROMECHANICAL 
METHOD OF MINIMIZING SERVO-MISSILE 
TRANSFER-FUNCTION VARIATIONS WITH FLIGHT 
CONDITION- Martin L. Nason. April 1958. 41p. 
diagrs., tabs. (NACA RM L56A31) 



FLIGHT INVESTIGATION OF THE EFFECTIVENESS 
OF AN AUTOMATIC AILERON TRIM CONTROL 
DEVICE FOR PERSONAL AIRPLANES. William H. 
Phillips, Helmut A. Kuehnel, and James B. Whitten. 
1957. ii, 15p. diagrs., photos. 
(NACA Rept. 1304. Supersedes TN 3637) 



AN ANALOG COMPUTER STUDY OF SEVERAL STA- 
BILITY AUGMENTATION SCHEMES DESIGNED TO 
ALLEVIATE ROLL-INDUCED INSTABILITY. Brent 
Y. Creer. February 1957. 50p. diagrs., tab. 
(NACA RM A56H30) 



TRANSITION-FLIGHT INVESTIGATION OF A 
FOUR-ENGINE-TRANSPORT VERTICAL-TARE - 
OFF AIRPLANE MODEL UTILIZING A LARGE 
FLAP AND EXTENSIBLE VANES FOR REDIRECT- 
ING THE PROPELLER SLIPSTREAM. Louis P. 
Tosti. December 1957. 35p. diagrs., photos., 
tab., film suppl. available on request. 
(NACA TN 4131) 



A FLIGHT INVESTIGATION OF THE EFFECTS OF 
VARIED LATERAL DAMPING ON THE EFFEC- 
TIVENESS OF A FIGHTER AIRPLANE AS A GUN 
PLATFORM. Helmut A. Kuehnel, Arnold R. 
Beckhardt, and Robert A. Champine. January 
1958. 30p. diagrs., photo., tabs. (NACA TN 4199. 
Supersedes RM L53F08a) 



APPLICATION OF STATISTICAL THEORY TO 
BEAM-RIDER GUIDANCE IN THE PRESENCE OF 
NOISE. H - MODIFIED WIENER FILTER THEORY. 
Elwood C. Stewart. June 1958. (i), 48p. diagrs., 
tabs. (NACA TN 4278. Supersedes RM A55Ella) 



(1.8.9) 
TRACKING 



MEASUREMENTS OF THE MOTIONS OF A LARGE 
SWEPT -WING ADIPLANE IN ROUGH AIR. Richard 
H. Rhyne. September 1958. 22p. diagrs., photo., 
tabs. (NACA TN 4310) 



( 1 ) AERODYNAMICS 



179 



(1.9) 
Aeroelasticity 



A COMPARISON OF THE AERODYNAMIC CHARAC- 
TERISTICS AT TRANSONIC SPEEDS OF FOUR 
WING-FUSELAGE CONFIGURATIONS AS DETER- 
MINED FROM DIFFERENT TEST TECHNIQUES 
Charles J. Etonian, BoydC. Myers. II. and Axel T 
Mattson. October 4, 1950. 66p. diagrs , photos., 
tabs (NACA RM L50H02) 



WING-ON AND WING-OFF LONGITUDINAL CHAR- 
ACTERISTICS OF AN AIRPLANE CONFIGURATION 
HAVING A THIN UNSWEPT TAPERED WING OF 
ASPECT RATIO 3, AS OBTAINED FROM ROCKET- 
PROPELLED MODELS AT MACH NUMBERS FROM 
0.8 TO 1.4. Clarence L. Gillis and A. James Vitale. 
March 14, 1951. 52p. diagrs., photos., tabs. 
(NACA RM L50K16) 



THE EFFECT OF VARIOUS MISSILE CHARACTER- 
ISTICS ON AIRFRAME FREQUENCY RESPONSE . 
Howard F. Matthews and Walter E . McNeill. 
January 1952. 16p. diagrs. (NACA RM A51L17a) 



LONGTTUDINAL STABILITY AND DRAG CHARAC- 
TERISTICS AT MACH NUMBERS FROM 0.75 TO 1.5 
OF AN AIRPLANE CONFIGURATION RAVING A 60° 
SWEPT WING OF ASPECT RATIO 2.24 AS OB- 
TAINED FROM ROCKET-PROPELLED MODELS. 
A. James Vitale, John C. McFall, Jr., and John D. 
Morrow. April 1952. 43p. diagrs., photos., tabs. 
(NACA RM L51K06) 



EFFECTS OF WING ELASTICITY ON THE AERO- 
DYNAMIC CHARACTERISTICS OF A 45° 
SWEPTBACK-WING-FUSELAGE COMBINATION 
MEASURED IN THE LANGLEY 8 -FOOT TRANSONIC 
TUNNEL. Robert S. Osborne and John P. Mugler, 
Jr. September 1952. 27p. diagrs., photos. 
(NACA RM L52G23) 



FREE -FLIGHT MEASUREMENTS OF SOME EF- 
FECTS OF SPOILER SPAN AND PROJECTION AND 
WING FLEXIBILITY ON ROLLING EFFECTIVENESS 
AND DRAG OF PLAIN SPOILERS ON A TAPERED 
SWEPTBACK WING AT MACH NUMBERS BETWEEN 
0.6 AND 1.6. Eugene D. Schult andE. M. Fields. 
October 1952. 30p. diagrs., photo., tab. 
(NACA RM L52H06a) 



LONGITUDINAL STABILITY, CONTROL EFFEC- 
TIVENESS, AND DRAG CHARACTERISTICS AT 
TRANSONIC SPEEDS OF A ROCKET -PROPELLED 
MODEL OF AN AIRPLANE CONFIGURATION 
HAVING AN UNSWEPT TAPERED WING OF ASPECT 
RATIO 3.0 AND NACA 65A004.5 AIRFOIL SECTIONS. 
JohnC. McFall, Jr., and James A. Hollinger. 
January 1953. 30p. diagrs., photos. 
(NACA RM L52L04) 



SOME APPROXIMATE METHODS FOR ESTIMATING 
THE EFFECTS OF AEROELASTIC BENDING OF 
ROCKET-PROPELLED MODEL-BOOSTER COMBI- 
NATIONS. Richard G. Arbic, George White, and 
Warren Gillespie, Jr. March 1953. 40p. diagrs., 
photos., tabs. (NACA RM L53A08) 



COMPARISON OF THE AERODYNAMIC CHARACTER- 
ISTICS AT TRANSONIC SPEEDS OF A PLANE WING 
AND A CAMBERED AND TWISTED WING, BOTH 
HAVING 45° OF SWEEPBACK AND AN ASPECT 
RATIO OF 6. George H. Holdaway. May 1953. 
49p. diagrs., photos. (NACA RM A53B16) 



INVESTIGATION OF WING FLUTTER AT TRAN- 
SONIC SPEEDS FOR SDC SYSTEMATICALLY VARIED 
WING PLAN FORMS. George W. Jones, Jr., and 
Hugh C. DuBose. August 1953. 32p. diagrs., 
photos., 3 tabs. (NACA RM L53G10a) 



AN ENGINEERING METHOD FOR THE DETER- 
MINATION OF AEROELASTIC EFFECTS UPON THE 
ROLLING EFFECTIVENESS OF AILERONS ON 
SWEPT WINGS. H. Kurt Strass and Emily W. 
Stephens. November 1953. 82p. diagrs., tabs. 
(NACA RM L53H14) 



COMPARISON OF EXPERIMENTAL WITH CALCU- 
LATED RESULTS FOR THE LIFTING EFFECTIVE- 
NESS OF A FLEXIBLE 45° SWEPTBACK WING OF 
ASPECT RATIO 6.0 AT MACH NUMBERS FROM 0.8 
TO 1.3. Richard E. Walters. April 1954. 35p. 
diagrs., photos., tab. (NACA RM L54B16) 



SOME EFFECTS OF AILERON SPAN, AILERON 
CHORD, AND WTNG TWIST ON ROLLING EFFEC- 
TIVENESS AS DETERMINED BY ROCKET- 
POWERED MODEL TESTS AND THEORETICAL 
ESTIMATES. H. Kurt Strass and Warren A. Tucker. 
September 1954. 29p. diagrs., photos., tabs. 
(NACA RM L54G13) 



LONGITUDINAL STABILITY CHARACTERISTICS AT 
TRANSONIC SPEEDS OF A CANARD CONFIGURA- 
TION HAVING A 45° SWEPTBACK WING OF ASPECT 
RATIO 6.0 AND NACA 65A009 AmFOIL SECTION. 
A. James Vitale and John C. McFall, Jr. November 
1954. 24p. diagrs., photos., tab. 
(NACA RM L54I01) 



FREE-FLIGHT INVESTIGATION, INCLUDING 
SOME EFFECTS OF WING AEROELASTICITY, OF 
THE ROLLING EFFECTIVENESS OF AN ALL- 
MOVABLE HORIZONTAL TAIL WITH DIFFEREN- 
TIAL INCIDENCE AT MACH NUMBERS FROM 0.6 
TO 1.5. Roland D. English. January 1955. lip. 
diagrs., photo. (NACA RM L54K30) 



STUDY OF SOME EFFECTS OF STRUCTURAL 
FLEXIBILITY ON THE LONGITUDINAL MOTIONS 
AND LOADS AS OBTAINED FROM FLIGHT MEAS- 
UREMENTS OF A SWEPT -WING BOMBER. James 
J. Donegan and Carl R. Huss. May 1955. 53p. 
diagrs., tabs. (NACA RM L54L16) 



THE EFFECT OF EXTERNAL STIFFENING RIBS ON 
THE ROLLING POWER OF AILERONS ON A SWEPT 
WTNG. Emily W. Stephens. October 1956. 15p. 
diagrs., photo., tab. (NACA RM L56D19) 



180 



(1) AERODYNAMICS 



AN ANALYSIS OF THE EFFECTS OF AEROELAS- 
TICITY ON STATIC LONGITUDINAL STABILITY 
AND CONTROL OF A SWEPT-WING AIRPLANE. 
Richard B. Skoog. 1957. ii, 12p. diagrs. 
(NACARept. 1298. Supersedes RM A51C19) 



ON PANEL FLUTTER AND DIVERGENCE OF IN- 
FINITELY LONG UNSTIFFENED AND RING- 
STIFFENED THIN-WALLED CIRCULAR CYLINDERS. 
Robert W. Leonard and John M. Hedgepeth. 1957. 
ii, 19p. diagrs. (NACARept. 1302. Supersedes 
TN 3638) 



EXPERIMENTAL AND PREDICTED LONGITUDINAL 
AND LATERAL-DIRECTIONAL RESPONSE CHAR- 
ACTERISTICS OF A LARGE FLEXIBLE 35° SWEPT- 
WING AIRPLANE AT AN ALTITUDE OF 35,000 FEET. 
Henry A. Cole, Jr., Stuart C. Brown, and Euclid C. 
Holleman.. 1957. 11, 39p. diagrs., photo., tabs. 
(NACARept. 1330. Supersedes RM A54H09; 
TN 3874) 



DETERMINATION OF LONGITUDINAL STABILITY 
AND CONTROL CHARACTERISTICS FROM FREE- 
FLIGHT MODEL TESTS WITH RESULTS AT TRAN- 
SONIC SPEEDS FOR THREE AIRPLANE CONFIGU- 
RATIONS. Clarence L. Gillis and Jesse L. Mitchell. 
1957. ii, 28p. diagrs., photos., tabs. 
(NACARept. 1337) 



WIND-TUNNEL INVESTIGATION OF THE STATIC 
LATERAL STABILITY CHARACTERISTICS OF 
WING-FUSELAGE COMBINATIONS AT HIGH SUB- 
SONIC SPEEDS. TAPER-RATIO SERIES. James 
W. Wiggins and Paul G. Fournier. October 1957. 
25p. diagrs., photos. (NACA TN 4174. Supersedes 
RM L53B25a) 



MEASURED AND PREDICTED DYNAMIC RESPONSE 
CHARACTERISTICS OF A FLEXIBLE AIRPLANE TO 
ELEVATOR CONTROL OVER A FREQUENCY RANGE 
INCLUDING THREE STRUCTURAL MODES. 
Henry A. Cole, Jr., and Euclid C. Holleman. 
February 1958. 81p. diagrs., photo., tabs. 
(NACA TN 4147) 



SOME MEASUREMENTS OF AERODYNAMIC 
FORCES AND MOMENTS AT SUBSONIC SPEEDS 
ON A RECTANGULAR WING OF ASPECT RATIO 2 
OSCILLATING ABOUT THE MIDCHORD. Edward 
Widmayer, Jr., Sherman A. Clevenson, and 
Sumner A. Leadbetter. May 1958. 45p. diagrs., 
tabs. (NACA TN 4240. Supersedes RM L53F19) 



FLUTTER ANALYSIS OF RECTANGULAR WINGS OF 
VERY LOW ASPECT RATIO. Robert W. Fralich 
and John M. Hedgepeth. June 1958. 24p. diagrs. 
(NACA TN 4245) 



ANALYTICAL AND EXPERIMENTAL INVESTIGA- 
TION OF AERODYNAMIC FORCES AND MOMENTS 
ON LOW -ASPECT-RATIO WINGS UNDERGOING 
FLAPPING OSCILLATIONS. Donald S. Woolston, 
Sherman A. Clevenson, and Sumner A. Leadbetter. 
August 1958. 25p. diagrs., tab. (NACA TN 4302) 



ON THE FLUTTER OF CYLINDRICAL SHELLS AND 
PANELS MOVING IN A FLOW OF GAS. (O Flatter e 
Tsilindrichesklkh Obolochek i Panelei 
Dvizhushchikhsia V Potoke Gaza.) R. D. Stepanov. 
September 1958. 25p. diagrs., tabs. (NACA TM 
1438. Translation from Prikladnaia Matematika i 
Mekhanika, v. 21, no. 5, 1957, p. 644-657) 



AN EXPERIMENTAL INVESTIGATION OF THE 
EFFECT OF VARIOUS PARAMETERS INCLUDING 
TIP MACH NUMBER ON THE FLUTTER OF SOME 
MODEL HELICOPTER ROTOR BLADES. George W. 
Brooks and John E. Baker. September 1958. 68p. 
diagrs., photo., tabs. (NACA TN 4005. Supersedes 
RM L53D24) 



MEASUREMENTS OF AERODYNAMIC FORCES AND 
MOMENTS AT SUBSONIC SPEEDS ON A SIMPLIFIED 
T-TAIL OSCILLATING IN YAW ABOUT THE FIN 
MroCHORD. Sherman A. Clevenson and Sumner A. 
Leadbetter. September 1958. 20p. diagrs., tab. 
(NACA TN 4402) 



181 



(1) AERODYNAMICS 



O.IO) 
Parachutes 



WIND-TUNNEL INVESTIGATION OF THE STABILITY 
OF THE JETTISONABLE NOSE SECTION OF THE 
XS-2 AIRPLANE. Stanley H. Scher and Roscoe H. 
Goodwin. October 14, 1948. 19p. dlagrs., photos., 
tabs. (NACA RM L8I14) 



SUMMARY OF SPIN AND RECOVERY CHARACTER- 
ISTICS OF 12 MODELS OF FLYING-WING AND 
UNCONVENTIONAL-TYPE AIRPLANES. Ralph W. 
Stone, Jr., and Burton E- Hultz, March 1, 1951. 
95p. diagrs., photo., tabs. (NACA RM L50L29) 



(2) 



(2) 
HYDRODYNAMICS 



183 



(2) HYDRODYNAMICS 



(2) 
HYDRODYNAMICS 



COMPARISON OF HYDRODYNAMIC -IMPACT 
ACCELERATION AND RESPONSE FOR SYSTEMS 
WITH SINGLE AND WITH MULTIPLE ELASTIC 
MODES. Robert W. Miller. February 1958. 30p. 
diagrs., photos., tabs. (NACA TN 4194) 



184 



(2) HYDRODYNAMICS 



(2.1) 
Theory 



COMPARISON WITH THEORY OF LANDING IM- 
PACTS OF A MODEL OF A SEAPLANE INCORPO- 
RATING A HYDRO-SKI WITH AND WITHOUT A 
SHOCK ABSORBER. Edward L. Hoffman. July 
1956. 30p. diagrs., photo., tabs. 
(NACA RM L56D26) 



THEORETICAL DETERMINATION OF LOW-DRAG 
SUPERCAVITATING HYDROFOILS AND THEIR 
TWO-DIMENSIONAL CHARACTERISTICS AT ZERO 
CAVITATION NUMBER. Virgil E. Johnson, Jr. 
September 1957. 29p. diagrs. (NACA RM L57Glla) 



IMPACT-LOADS INVESTIGATION OF CHTNE- 
IMMERSED MODEL HAVING A CIRCULAR-ARC 
TRANSVERSE SHAPE. Philip M. Edge, Jr. 
September 1957. 35p, diagrs., photo., tab. 
(NACA TN 4103) 



IMPACT-LOADS INVESTIGATION OF A CHINE- 
IMMERSED MODEL HAVING A LONGITUDINALLY 
CURVED BOW AND A V-BOTTOM WITH A DEAD- 
RISE ANGLE OF 30°. Philip M. Edge, Jr., and 
John S. Mixson. September 1957. 24p. diagrs., 
photo., tabs. (NACA TN 4106) 



ROUGH-WATER IMPACT -LOAD INVESTIGATION OF 
A CHINE -IMMERSED V-BOTTOM MODEL HAVING 
A DEAD -RISE ANGLE OF 10°. Melvin F. Markey 
and Thomas D. Carpinl. October 1957. 32p. 
diagrs., photos., tab. (NACA TN 4123) 



THEORETICAL AND EXPERIMENTAL INVESTIGA- 
TION OF ARBITRARY ASPECT RATIO, SUPER- 
CAVITATING HYDROFOILS OPERATING NEAR THE 
FREE WATER SURFACE. Virgil E. Johnson, Jr. 
December 1957. 94p. diagrs., photos. 
(NACARML57I16). 



A METHOD FOR CALCULATION OF HYDRO- 
DYNAMIC LIFT FOR SUBMERGED AND PLANING 
RECTANGULAR LIFTING SURFACES. Kenneth L. 
Wadlin and Kenneth W. Christopher. January 
1958. 34p. diagrs. (NACA TN 4168) 



IMPACT ON A COMPRESSIBLE FLUID. (Udar o 
szhimaemuiu zhldkost. ) I. T. Egorov. February 
1958. 12p. diagrs. (NACA TM 1413. Translation 
from Prikl adnata Matematika i Mekhanika, v. 20, 
no. 1,1956, p. 67-72) 



HYDRODYNAMIC IMPACT LOADS OF A -20<> DEAD- 
RISE INVERTED-V MODEL AND COMPARISONS 
WITH LOADS OF A FLAT -BOTTOM MODEL. 
Philip M. Edge, Jr. August 1958. 36p. diagrs., 
photo., tabs. (NACA TN 4339) 



WATER-IMPACT THEORY FOR AIRCRAFT 
EQUIPPED WITH NONTRIMMING HYDRO-SKIS 
MOUNTED ON SHOCK STRUTS. Emanuel Schnitzer. 
September 1958. 29p. diagrs. (NACA TN 4256. 
Supersedes RM L54H10) 

HYDRODYNAMIC IMPACT LOADS ON 30° AND 60° 
V-STEP PLAN -FORM MODELS WITH AND WITHOUT 
DEAD RISE. Philip M. Edge, Jr., and Jean P. 
Mason. September 1958. 20p. diagrs., photos., 
tab. (NACA TN 4401) 



185 



(2) HYDRODYNAMICS 



(2.2) 
General Arrangement Studies 



CONSIDERATIONS AFFECTING HYDRO-SKI AIR- 
PLANE DESIGN. Kenneth L. Wadlin. November 
1953, 14p. diagrs. (NACA RM L53I28b) 



THE HYDRODYNAMIC PLANING LIFT OF FOUR 
SURFACES AS MEASURED IN A 200-FPS FREE JET. 
John R. McGehee, Bernard Weinflash, and Charles 
A. Pelz. July .1954. 24p. diagrs., photos. 
(NACA RM L54F01) 



COMPARISON WITH THEORY OF LANDING IM- 
PACTS OF A MODEL OF A SEAPLANE INCORPO- 
RATING A HYDRO-SKI WITH AND WITHOUT A 
SHOCK ABSORBER. Edward L. Hoffman. July 
1956. 30p. diagrs., photo., tabs. 
{NACA RM L56D26) 



EFFECT OF INCREASE IN ANGLE OF DEAD RISE 
ON THE HYDRODYNAMIC QUALITIES OF A SEA- 
PLANE CONFIGURATION INCORPORATING HIGH 
WING LOADING. Walter J. Kapryan and Irving 
Weinstein. October 1956. 3lp. diagrs., photos., 
tabs. (NACA RM L56H21) 



TANK INVESTIGATION OF A SERIES OF RELATED 
HYDRO-SKIS AS LOAD-ALLEVIATION DEVICES 
FOR LANDING A SEAPLANE IN WAVES. Arthur W. 
Carter, Archibald E. Morse, Jr., and David R. 
Woodward. December 1956, 33p. diagrs., tabs. 
(NACA RM L56I25a) 



ROUGH-WATER IMPACT -LOAD INVESTIGATION OF 
A CHINE -IMMERSED V -BOTTOM MODEL HAVING 
A DEAD-RISE ANGLE OF 10°. Melvln F. Markey 
and Thomas D. Carpini. October 1957. 32p. 
diagrs., photos., tab. (NACA TN 4123) 



THEORETICAL AND EXPERIMENTAL INVESTIGA- 
TION OF ARBITRARY ASPECT RATIO, SUPER- 
CAVITATING HYDROFOILS OPERATING NEAR THE 
FREE WATER SURFACE. Virgil E. Johnson, Jr. 
December 1957. 94 p. diagrs., photos. 
(NACA RML57I16) 



A METHOD FOR CALCULATION OF HYDRO- 
DYNAMIC LIFT FOR SUBMERGED AND PLANING 
RECTANGULAR LIFTING SURFACES. Kenneth L. 
Wadlin and Kenneth W. Christopher. January 
1958. 34p. diagrs. (NACA TN 4168) 



AN EXPERIMENTAL INVESTIGATION OF WAKE 
EFFECTS ON HYDRO-SKIS. Ellis E. McBride and 
Lloyd J. Fisher. May 1958. 34p. diagrs., photos., 
tab. (NACA TN 4251) 



WATER-IMPACT THEORY FOR AIRCRAFT 
EQUIPPED WITH NONTRIMMING HYDRO-SKIS 
MOUNTED ON SHOCK STRUTS. Emanuel Schnitzer. 
September 1958. 29p. diagrs. (NACA TN 4256. 
Supersedes RM L54H10) 



186 



(2) HYDRODYNAMICS 



(2.3) 
Seaplane Hull Variables 



CONSIDERATIONS AFFECTING HYDRO-SKI AIR- 
PLANE DESIGN. Kenneth L. Wadlin. November 
1953. 14p. diagrs. (NACA RM L5 3128b) 



IMPACT-LOADS INVESTIGATION OF CHINE- 
IMMERSED MODEL HAVING A CIRCULAR-ARC 
TRANSVERSE SHAPE. Philip M. Edge, Jr. 
September 1957. 35p. diagrs., photo., tab. 
(NACA TN 4103) 



HYDRODYNAM1C IMPACT LOADS OF A -200 DEAD- 
RISE INVERTED-V MODEL AND COMPARISONS 
WITH LOADS OF A FLAT-BOTTOM MODEL. . 
Philip M. Edge, Jr. August 1958. 36p. diagrs., 
photo., tabs. (NACA TN 4339) 



HYDRODYNAMIC IMPACT LOADS ON 30° AND 60° 
V-STEP PLAN-FORM MODELS WITH AND WITHOUT 
DEAD RISE. Philip M. Edge, Jr., and Jean P. 
Mason. September 1958. 20p. diagrs., photos., 
tab. (NACA TN 4401) 



(2.3.1) 
LENGTH-BEAM RATIO 



THE HYDRODYNAMIC PLANING LIFT OF FOUR 
SURFACES AS MEASURED IN A 200-FPS FREE JET. 
John R. McGehee, Bernard Weinf lash, and Charles 
A. Pelz. July 1954. 24p. diagrs., photos. 
(NACA RM L54F01) 



TANK INVESTIGATION OF A SERIES OF RELATED 
HYDRO -SKIS AS LOAD-ALLEVIATION DEVICES 
FOR LANDING A SEAPLANE IN WAVES. Arthur W. 
Carter, Archibald E. Morse, Jr., and David R. 
Woodward. December 1956. 33p. diagrs., tabs. 
(NACA RM L56I25a) 



(2.3.2) 
DEAD RISE 



EFFECT OF INCREASE IN ANGLE OF DEAD RISE 
ON THE HYDRODYNAMIC QUALITIES OF A SEA- 
PLANE CONFIGURATION INCORPORATING HIGH 
WING LOADING. Walter J. Kapryan and Irving 
We in stein. October 1956. 31p. diagrs., photos., 
tabs. (NACA RM L56H21) 



HIGH-SPEED HYDRODYNAMIC CHARACTERISTICS 
OF A FLAT PLATE AND 20° DEAD-RISE SURFACE 
IN UNSYMMETRICAL PLANING CONDITIONS. 
Daniel Savltsky, R. E. Prowse, and D. H. Lueders, 
Stevens Institute of Technology. June 1958 t 93p. 
diagrs., photos., tabs. (NACA TN 4187) 



(2.3.5) 
FOREBODY SHAPE 



IMPACT-LOADS INVESTIGATION OF A CHINE- 
IMMERSED MODEL HAVING A LONGITUDINALLY 
CURVED BOW AND A V-BOTTOM WITH A DEAD- 
RISE ANGLE OF 30°. Philip M. Edge, Jr., and 
John S. Mixson. September 1957. 24p. diagrs., 
photo., tabs. (NACA TN 4106) 



(2.3.6) 
CHINES 



THE HYDRODYNAMIC PLANING LIFT OF FOUR 
SURFACES AS MEASURED IN A 200-FPS FREE JET. 
John R. McGehee, Bernard Weinf lash, and Charles 
A. Pelz. July 1954. 24p. diagrs., photos. 
(NACA RM L54F01) 



HIGH-SPEED HYDRODYNAMIC CHARACTERISTICS 
OF A FLAT PLATE AND 20° DEAD-RISE SURFACE 
IN UNSYMMETRICAL PLANING CONDITIONS. 
Daniel Savitsky, R. E. Prowse, and D. H. Lueders, 
Stevens Institute of Technology. June 1958. 93p. 
diagrs., photos., tabs. (NACA TN 4187) 



187 



(2) HYDRODYNAMICS 



(2.6) 
Planing Surfaces 



CONSIDERATIONS AFFECTING HYDRO-SKI AIR- 
PLANE DESIGN. Kenneth L. Wadlin. November 
1953. 14p. diagrs. (NACA RM L53I28b) 



THE HYDRODYNAMIC PLANING LIFT OF FOUR 
SURFACES AS MEASURED IN A 200-FPS FREE JET. 
John R. McGehee, Bernard Weinflash, and Charles 
A. Pelz. July 1954. 24p. diagrs., photos. 
(NACA RM L54F01) 



COMPARISON WITH THEORY OF LANDING IM- 
PACTS OF A MODEL OF A SEAPLANE INCORPO- 
RATING A HYDRO-SKI WITH AND WITHOUT A 
SHOCK ABSORBER. Edward L. Hoffman. July 
1956. 30p. diagrs., photo., tabs. 
(NACA RM L56D26) 



TANK INVESTIGATION OF A SERIES OF RELATED 
HYDRO-SKIS AS LOAD -ALL EVIATION DEVICES 
FOR LANDING A SEAPLANE IN WAVES. Arthur W. 
Carter, Archibald E. Morse, Jr., and David R. 
Woodward. December 1956. 33 p. diagrs., tabs. 
(NACA RM L56I25al 



INVESTIGATION OF THE INFLUENCE OF THE 
BOUNDARIES OF A HIGH-SPEED FREE WATER JET 
ON THE PLANING LIFT OF A FLAT PLATE. John 
R. McGehee. March 1957. 21p. diagrs., photos. 
(NACA RM L56K02) 



EFFECT OF BOUNDARY SOLIDITY ON PLANING 
LIFT OBTAINED IN A HIGH-SPEED WATER JET 
WITH A SINGLE LONGITUDINAL SLOT IN EACH 
RIGID BOUNDARY. Bernard Weinflash. October 
1957. 27p. diagrs., photos. (NACA RM L57I06) 



ROUGH-WATER IMPACT -LOAD INVESTIGATION OF 
A CHINE -IMMERSED V-BOTTOM MODEL HAVING 
A DEAD-RISE ANGLE OF 10°. Melvin F. Markey 
and Thomas D. Carpinl. October 1957. 32p. 
diagrs., photos., tab. (NACA TN 4123) 



THEORETICAL AND EXPERIMENTAL INVESTIGA- 
TION OF ARBITRARY ASPECT RATIO, SUPER- 
CAVTTATING HYDROFOILS OPERATING NEAR THE 
FREE WATER SURFACE. Virgil E. Johnson, Jr. 
December 1957. 94 p. diagrs., photos. 
(NACA RM L57I161 



A METHOD FOR CALCULATION OF HYDRO- 
DYNAMIC LIFT FOR SUBMERGED AND PLANING 
RECTANGULAR LIFTING SURFACES. Kenneth L, 
Wadlin and Kenneth W. Christopher. January 
1958. 34p. diagrs. (NACA TN 4168) 



AN EXPERIMENTAL INVESTIGATION OF WAKE 
EFFECTS ON HYDRO-SKIS. Ellis E. McBrlde and 
Lloyd J. Fisher. May 1958. 34p. diagrs., photos., 
tab. (NACA TN 4251) 



HIGH-SPEED HYDRODYNAMIC CHARACTERISTICS 
OF A FLAT PLATE AND 20° DEAD-RISE SURFACE 
IN UNSYMMETRICAL PLANING CONDITIONS. 
Daniel Savitsky, R. E. Prowse, and D. H. Lueders, 
Stevens Institute of Technology. June 1958. 93p. 
diagrs., photos., tabs. (NACA TN 4187) 



EFFECTS OF NOSE SHAPE AND SPRAY CONTROL 
STRIPS ON EMERGENCE AND PLANING SPRAY OF 
HYDRO-SKI MODELS. John R. McGehee. July 
1958. 28p. diagrs., photos. (NACA TN 4294) 



188 



(2) HYDRODYNAMICS 



(2-7) 
Hydrofoils 



THEORETICAL DETERMINATION OF LOW-DRAG 
SUPERCAVITATING HYDROFOILS AND THEIR 
TWO-DIMENSIONAL CHARACTERISTICS AT ZERO 
CAVITATION NUMBER. Virgil E. Johnson, Jr. ' 
September 1957. 29p. diagrs. (NACA RM L57G1U) 



THEORETICAL AND EXPERIMENTAL INVESTIGA- 
TION OF ARBITRARY ASPECT RATIO, SUPER- 
CAVITATING HYDROFOILS OPERATING NEAR THE 
FREE WATER SURFACE. Virgil E. Johnson, Jr. 
December 1957. 94 p. diagrs., photos. 
fNACA RML57I16). 



A METHOD FOR CALCULATION OF HYDRO- 
DYNAMIC LIFT FOR SUBMERGED AND PLANING 
RECTANGULAR LIFTING SURFACES. Kenneth L. 
Wadlin and Kenneth W. Christopher. January 
1958. 34 p, diagrs. (NACA TN 4168) 



189 



(2) HYDRODYNAMICS 



Surface Craft 



WATER-IMPACT THEORY FOR AIRCRAFT 
EQUIPPED WITH NONTRIMMING HYDRO-SKIS 
MOUNTED ON SHOCK STRUTS. Emanuel Schnitzer. 
September 1958. 29p. diagrs. (NACA TN 4256. 
Supersedes RM L54H10) 



190 

(2) HYDRODYNAMICS 



(2.9) 
Ditching Characteristics 



DITCHING INVESTIGATIONS OF DYNAMIC MODELS 
AND EFFECTS OF DESIGN PARAMETERS ON 
DITCHING CHARACTERISTICS. Lloyd J. Fisher 
and Edward L. Hoffman. 1958. ii, J8p. dlagrs., 
tabs, (NACARept. 1347. Supersedes TN 3946) 



(2) HYDRODYNAMICS 



191 



(2-10) 
Stability and Control 



HIGH-SPEED HYDRODYNAMIC CHARACTERISTICS 
OF A FLAT PLATE AND 20° DEAD-RISE SURFACE 
IN. UNSYMMETRICAL PLANING CONDITIONS. 
Daniel Savitsky, R. E, Prowse, and D. H. Lueders, 
Stevens Institute of Technology. June 1958. 93p. 
diagrs., photos., tabs. (NACA TN 4187) 



(3) 



(3) 
PROPULSION 



193 



(3) PROPULSION 



(3) 
PROPULSION 



ANALYSIS OF SEVERAL METHODS OF PUMPING 
COOLING AIR FOR TURBOJET -ENGINE AFTER- 
BURNERS. John C. Samuels and Herbert Yanowitz. 
February 1953. 54p. diagrs. (NACA RM E52K26) 



ENGINEERING METHOD OF RAM-JET THRUST 
DETERMINATION BASED ON EXPERIMENTALLY 
OBTAINED COMBUSTOR PARAMETERS. 
H. Rudolph Dettwyler and Maxime A. Faget. August 
1953. 44p. diagrs., tab. (NACA RM L53E*1) 



AN ANALYSIS OF THE TRANSONIC AND SUPER- 
SONIC PERFORMANCE OF SEVERAL FDCED- 
GEOMETRY AIR INLETS. Robert E. Pendley and 
Robert R. Howell. March 1955. 30p. diagrs., 
tab. (NACARML54L29) 



SCREEN-TYPE NOISE REDUCTION DEVICES FOR 
GROUND RUNNING OF TURBOJET ENGINES. 
Willard D. Coles and Warren J. North. July 1957. 
23p. diagrs., photos. (NACA TN 4033) 



194 



(3) PROPULSION 



(3.1) 
Complete Systems 



EFFECT OF FUEL DENSITY AND HEATING VALUE 
ON RAM -JET AIRPLANE RANGE. Hugh M. 
Henneberry. February 1952. 56p. diagrs., tabs. 
(NACA RM E51L21) 



ANALYTICAL COMPARISON OF TURBINE-BLADE 
COOLING SYSTEMS DESIGNED FOR A TURBOJET 
ENGINE OPERATING AT SUPERSONIC SPEED AND 
HIGH ALTITUDE. I - LIQUID -COO LING SYSTEMS. 
Wilson B. Schramm, Alfred J. Nachtigall, and 
Vernon L. Arne. January 1953. 52p. diagrs., 
tabs . (NACA RM E 52J 29) 



ANALYTICAL COMPARISON OF TURBINE-BLADE 
COOLING SYSTEMS DESIGNED FOR A TURBOJET 
ENGINE OPERATING AT SUPERSONIC SPEED AND 
HIGH ALTITUDE. U - AIR-COOLING SYSTEMS. 
Wilson B. Schramm, Vernon L. Arne, and Alfred J. 
Nachtigall. January 1953. 50p. diagrs., tabs. 
(NACARME52J30) 



ANALYSIS OF SEVERAL METHODS OF PUMPING 
COOLING AIR FOR TURBOJET -ENGINE AFTER- 
BURNERS. John C. Samuels and Herbert Yanowitz. 
February 1953. 54p. diagrs. (NACA RM E52K26) 



ENGINEERING METHOD OF RAM -JET THRUST 
DETERMINATION BASED ON EXPERIMENTALLY 
OBTAINED COMBUSTOR PARAMETERS. 
H. Rudolph Dettwyler and Majdme A. Faget. August 
1953. 44p. diagrs., tab. (NACA RM L53E21) 



INVESTIGATION OF A FLOW DEFLECTOR AND AN 
AUXILIARY SCOOP FOR IMPROVING OFF-DESIGN 
PERFORMANCE OF NOSE INLETS. Warren E. 
Anderson and Richard Scherrer. July 1954. 32p. 
diagrs., photos. (NACA RM A54E06) 



FLIGHT AND PREFLIGHT TESTS OF A RAM JET 
BURNING MAGNESIUM SLURRY FUEL AND 
UTILIZING A SOLID-PROPELLANT GAS GENERA- 
TOR FOR FUEL EXPULSION. Walter A. Bartlett, 
Jr., and William K. Hagginbothom, Jr. April 1955. 
35p. diagrs., photos. (NACA RM L55A24) 



PREFLIGHT AND FLIGHT-TEST INVESTIGATION 
OF A 50-PERCENT-MAGNESnjM 50-PERCENT 
JP-4 SLURRY FUEL IN A TWIN -ENGINE RAM- JET 
VEHICLE. Otto F. Trout, Jr., and Thomas L. 
Kennedy. May 1956. 27p. diagrs., photos. 
(NACA RM L56C06) 



TABLES AND CHARTS FOR THERMODYNAMIC 
CALCULATIONS INVOLVING AIR AND FUELS CON- 
TAINING BORON, CARBON, HYDROGEN, AND 
OXYGEN . Eldon W . Hall and Richard J . Weber . 
July 1956. 82p. diagrs., tabs. (NACA RM E56B27) 



AN ANALOG STUDY OF A SHOCK- POSITION DIF- 
FUSER CONTROL ON A SUPERSONIC TURBOJET 
ENGINE. David Novik. August 1956. 27p. diagrs. 
(NACA RM E56E09a) 



COMPATIBILITY OF METALS WITH LIQUID FLUO- 
RINE AT HIGH PRESSURES AND FLOW VELOCITIES. 
Harold W. Schmidt. July 1958. 15p. diagrs., 
photo., tab. (NACA RM E58D11) 



(3.1.3) 
TURBOJET ENGINES 



ALTITUDE-WIND-TUNNEL INVESTIGATION OF 
TAIL-PIPE BURNER WITH CONVERGING CONICAL 
BURNER SECTION ON J35-A-5 TURBOJET ENGINE. 
H. Carl Thorman and Carl E. Campbell. 
February 10, 1950. 60p. diagrs., photos., tab. 
(NACA RM E9I16) 



ANALYTICAL AND EXPERIMENTAL INVESTIGA- 
TION OF THRUST AUGMENTATION OF AXIAL- 
AND CENTRIFUGAL-COMPRESSOR TURBOJET 
ENGINES BY INJECTION OF WATER AND ALCO- 
HOL IN COMBUSTION CHAMBERS. David S. 
Gabriel, Harry W. Dowman, and William L. Jones. 
April 13, 1950. 43p. diagrs., photo. 
(NACA RM E9K29) 



ALTITUDE PERFORMANCE AND OPERATIONAL 
CHARACTERISTICS OF 29-INCH -DIAMETER TAIL- 
PIPE BURNER WITH SEVERAL FUEL SYSTEMS 
AND FUEL-COOLED STAGE-TYPE FLAME 
HOLDERS ON J35-A-5 TURBOJET ENGINE. 
Richard L. Golladay and Harry E. Bloomer. 
April 28, 1950. 57p. diagrs., photos., tab. 
(NACA RM E50A19) 



TURBOJET COMBUSTOR EFFICIENCY AT HIGH 
ALTITUDES. Walter T. Olson, J. Howard Chllds, 
and Edmund R. Jonash. October 27, 1950. 51p. 
diagrs., photo. (NACA RM E50I07) 



NACA INVESTIGATIONS OF ICING-PROTECTION 
SYSTEMS FOR TURBOJET-ENGINE INSTALLA- 
TIONS. Uwe von Glahn, Edmund E. Callaghan, and 
Vernon H. Gray. May 2, 1951. (ii), 83p. diagrs., 
photos. (NACA RM E51B12) 



LOITERING AND RANGE PERFORMANCE OF 
TURBOJET-POWERED AIRCRAFT DETERMINED 
BY OFF-DESIGN ENGINE CYCLE ANALYSIS. 
Stanley L. Koutz and Reece V. Hensley. 
February 1952. 45p. diagrs., tab. 
(NACARME51K29) 



ALTITUDE PERFORMANCE INVESTIGATION OF 
TWO FLAME -HOLDER AND FUEL-SYSTEM CON- 
FIGURATIONS IN SHORT AFTERBURNER. S. C. 
Huntley and H. D. Wilsted. May 1952. 41p. 
diagrs., photos., tab. (NACA RM E52B25) 



ALTITUDE PERFORMANCE INVESTIGATION OF 
SINGLE- AND DOUBLE -ANNULAR TURBOJET- 
ENGINE COMBUSTORS WITH VARIOUS SIZE FUEL 
NOZZLES. James L. Harp, Jr., and Kenneth R. 
Vincent. June 1952. 60p. photos., diagrs., tab. 
(NACARME51L14) 



(3) propulsion; 



195 



COMPONENT AND OVER -ALL PERFORMANCE 
EVALUATION OF AN AXIAL-FLOW TURBOJET 
ENGINE OVER A RANGE OF ENGINE -INLET 
REYNOLDS NUMBERS. Curtis L. Walker, S-* C. 
Huntley, andW. M. Braithwaite. July 1952. 42p. 
diagrs., tabs. (NACA RM E52B08) 



EFFECT OF WATER VAPOR ON COMBUSTION OF 
MAGNESIUM-HYDROCARBON SLURRY FUELS IN 
SMALL-SCALE AFTERBURNER. Leonard K. 
Tower. October 1952. 39p. diagrs., tabs, i 
(NACA RM E52H25) 



ANALYTICAL COMPARISON OF TURBINE-BLADE 
COOLING SYSTEMS DESIGNED FOR A TURBOJET 
ENGINE OPERATING AT SUPERSONIC SPEED AND 
HIGH ALTITUDE. I - LIQUID-COOLING SYSTEMS. 
Wilson B. Schramm, Alfred J. Nachtigall, and 
Vernon L. Arne. January 1953. 52p. diagrs., 
tabs. (NACA RM E52J29) 



ANALYTICAL COMPARISON OF TURBINE-BLADE 
COOLING SYSTEMS DESIGNED FOR A TURBOJET 
ENGINE OPERATING AT SUPERSONIC SPEED A*ND 
HIGH ALTITUDE . H - AIR-COOLING SYSTEMS . 
Wilson B. Schramm, Vernon L. Arne, and Alfred J. 
Nachtigall. January 1953. 50p. diagrs., tabs. 
(NACARME52J30) 



ANALYSIS OF SEVERAL METHODS OF PUMPING 
COOLING AIR FOR TURBOJET- ENGINE AFTER- 
BURNERS. John C. Samuels and Herbert Yanowitz. 
February 1953. 54 p. diagrs. (NACA RM E52K26) 



ALTITUDE STARTING CHARACTERISTICS OF AN 
AFTERBURNER WITH AUTOKNTTsON AND HOT- 
STREAK IGNITION. P. E. Renas, R. W. Harvey, 
Sr., and E. T. Jansen. April 1953. 25p. diagrs., 
photos., tab. (NACARME53B02) 



INVESTIGATION OF A 10 -STAGE SUBSONIC AXIAL- 
FLOW RESEARCH COMPRESSOR, HI - INVESTI- 
GATION OF ROTATING STALL, BLADE VIBRATION, 
AND SURGE AT LOW AND INTERMEDIATE COM- 
PRESSOR SPEEDS. Merle C. Huppert, Eleanor L. 
Costllow, and Ray E. Budlnger. May 1953. 47p. 
diagrs., photos., tabs. (NACA RM E53C19) 



PRELIMINARY EXPERIMENTAL INVESTIGATION 
OF TRANSPIRATION COOLING FOR AN AFTER- 
BURNER WITH A SINTERED, POROUS STAINLESS- 
STEEL COMBUSTION -CHAMBER WALL. William 
K. Koffel. June 1953. 47p. diagrs., photos., tabs. 
(NACA RM E53D08) 



EFFECT OF DIFFUSER DESIGN, DIFFUSER-EX3T 
VELOCITY PROFILE, AND FUEL DISTRIBUTION 
ON ALTITUDE PERFORMANCE OF SEVERAL 
AFTERBURNER CONFIGURATIONS. E. William 
Conrad, Frederick W. Schulze, and Karl H. Usow. 
July 1953. 63p. diagrs., photos., tab. 
(NACA RM E53A30) 



DYNAMIC CHARACTERISTICS OF A SINGLE - 
SPOOL TURBOJET ENGINE. R. T. Craig, George 
Vasu, and R. D. Schmidt. August 1953. 50p. 
diagrs tab. (NACA RM E53C17) 



ALUMINUM BOROHYDR1DE AS AN IGNITION 
SOURCE FOR TURBOJET COMBUSTORS. David M. 
Straight, Edward A. Fletcher, and Hampton H. 
Foster. September 1953. 19p. diagrs., photos., 
tabs. (NACA RM E53G15) 



EXPERIMENTAL INVESTIGATION OF SCREECHING 
COMBUSTION IN FULL-SCALE AFTERBURNER. 
Karl H. Usow, Carl L. Meyer, and Frederick W. 
Schulze. December 1953. 62p. diagrs., photos., 
tab. (NACA RM E53I01) 



GENERAL CONSIDERATIONS OF MACH NUMBER 
EFFECTS ON COMPRESSOR- BLADE DESIGN. 
John F. Klapproth. April 1954. 24p. diagrs., 
photos. (NACA RM E53L23a) 



EXPERIMENTAL INVESTIGATION OF ROTATING 
STALL AND BLADE VIBRATION IN THE AXIAL - 
FLOW COMPRESSOR OF A TURBOJET ENGINE. 
Merle C. Huppert, Howard F. Calvert, and Andre J. 
Meyer. April 1954. 24p. diagrs., tabs. 
(NACA RM E54A08) 



PRELIMINARY INVESTIGATION OF PUMPING AND 
THRUST CHARACTERISTICS OF FULL-SIZE 
COOLING-AIR EJECTORS AT SEVERAL EXHAUST- 
GAS TEMPERATURES. W. K. Greathoutt. April 
1954. 130p. diagrs., photos., tab. 
(NACA RM E54A18) 



INVESTIGATION OF A TRANSLATING -CONE INLET 
AT MACH NUMBERS FROM 1.5 TO 2.0. L. Abbott 
Leissler and William H. Sterbentz. May 1954. 29p. 
diagrs., photos., tab. (NACA RM E54B23) 



ANALYSIS OF FACTORS AFFECTING SELECTION 
AND DESIGN OF Ant-COOLED SINGLE-STAGE 
TURBINES FOR TURBOJET ENGINES. I - TUR- 
BINE PERFORMANCE AND ENGINE WEIGHT-FLOW 
CAPACITY. Richard J. Rossbach, Wilson B. 
Schramm, and James E. Hubbartt. May 1954. 50p. 
diagrs., tab. (NACA RM E54C22) 



CHARACTERISTICS OF A HYDRAULIC CONTROL 
DETERMINED FROM TRANSIENT DATA OBTAINED 
WITH A TURBOJET ENGINE AT ALTITUDE. 
George Vasu, William L. Hinde, and R. T. Craig. 
June 1954. 62p. diagrs., photo., tab. 
(NACA RM E53D02) 



ANALYSIS OF FACTORS AFFECTING SELECTION 
AND DESIGN OF AIR-COOLED SINGLE-STAGE 
TURBINES FOR TURBOJET ENGINES. II - 
ANALYTICAL TECHNIQUES. Richard J. Rossbach. 
June 1954. 29p. diagrs. (NACA RM E54D21) 



COOLING CHARACTERISTICS OF A 
TRANSPIRATION-COOLED AFTERBURNER WITH A 
POROUS WALL OF BRAZED AND ROLLED WIRE 
CLOTH. William K. Koffel. August 1954. 68p. 
diagrs., photos., tabs. (NACA RM E54E25) 



AN EVALUATION OF TURBOJET ENGINE THRUST 
CONTROL BY EXHAUST-NOZZLE-AREA MODULA- 
TION AND COMPRESSOR-INLET THROTTLING. 
James L. Harp, Jr., Wallace W. Velie, and William 
E. Mallett. August 1954. 17p. diagrs., photos. 
(NACA RM E54F21) 



LOW-PRESSURE PERFORMANCE OF EXPERIMEN- 
TAL PREVAPORIZING TUBULAR COMBUSTOR 
USING APPROXIMATELY STOICHIOMETRIC AD- 
MISSION OF FUEL-AIR MIXTURE INTO THE PRI- 
MARY ZONE. Robert R. fllbbard, Allen J. Metzler, 
and Wilfred E. Scull. August 1954. 38p. diagrs., 
tabs. (NACA RM E54F25a) 



196 



(3) PROPULSION 



PERFORMANCE OF A PAIR' OF TUBULAR COMBUS- 
TORS WITH AN EXTERNAL PILOT CHAMBER. 
Robert Friedman and Eugene V. Zettle. September 
1954. 26p. diagrs., tab. (NACA RM E54E11) 



ANALYSIS OF FACTORS AFFECTING SELECTION 
AND DESIGN OF AIR-COOLED SINGLE-STAGE 
TURBINES FOR TURBOJET ENGINES. HI - 
ENGINE DESIGN-POINT PERFORMANCE. James 
E. Hubbartt, Richard J. Rossbach, and Wilson B. 
Schramm. September 1954. 41p. diagrs., tab. 
(NACA RM E54F16a) 



PHOTOGRAPHIC INVESTIGATION OF AIR-FLOW 
PATTERNS IN TRANSPARENT ONE-SIXTH SECTOR 
OF ANNULAR TURBOJET-ENGINE COMBUSTOR 
WITH AXIAL-SLOT-TYPE AIR ADMISSION. 
Charles C. Graves and J. Dean Gernon. December 
1954. 24p. diagrs., photos. (NACA RM E 54128a) 



PRELIMINARY INVESTIGATION OF THE STRENGTH 
AND ENDURANCE OF PLASTIC-IMPREGNATED 
FIBERGLASS COMPRESSOR BLADES. Donald F. 
Johnson and Andre J. Meyer, Jr. January 1955. 
21p. diagrs., photos. (NACA RM E54I27a) 



ALUMINUM BOROHYDRIDE - HYDROCARBON MIX- 
TURES AS A SOURCE OF IGNITION FOR A TURBO- 
JET COMBUSTOR. Hampton H. Foster, Edward A. 
Fletcher, and David M. Straight. February 1955. 
24p. diagrs., photo., tabs. (NACA RM E54K12) ' 



AN ANALYSIS OF THE TRANSONIC AND SUPER- 
SONIC PERFORMANCE OF SEVERAL FIXED- 
GEOMETRY AIR INLETS. Robert E . Pendley and 
Robert R. Howell. March 1955. 36p. diagrs., 
tab. (NACARML54L29) 



ANALYSIS OF FACTORS AFFECTING SELECTION 
AND DESIGN OF AIR-COOLED SINGLE-STAGE 
TURBINES FOR TURBOJET ENGINES. F7 - 
COOLANT-FLOW REQUIREMENTS AND PER- 
FORMANCE OF ENGINES USING AIR-COOLED 
CORRUGATED-INSERT BLADES. Henry O. Slone 
and James E. Hubbartt. May 1955. 45p, diagrs., 
photos., tab. (NACA RM E55C09) 



STEADY-STATE AND SURGE CHARACTERISTICS 
OF A COMPRESSOR EQUIPPED WITH VARIABLE 
INLET GUIDE VANES OPERATING IN A TURBOJET 
ENGINE. Lewis E. Wallner and Robert J. Lubick. 
June 1955. 54p. diagrs., photos. (NACA RM E54I28) 



COMPRESSOR-BLADE VIBRATION AND PERFORM- 
ANCE IN A J47-23 TURBOJET ENGINE UNDER 
CONDITIONS OF ROTATING STALL . Morgan P . 
Hanson, Donald F. Johnson, and Andre J. Meyer, Jr. 
June 1955. 18p. diagrs., tab. (NACA RM E54L20a) 



ANALYTIC EVALUATION OF EFFECT OF INLET- 
AIR TEMPERATURE AND COMBUSTION PRESSURE 
ON COMBUSTION PERFORMANCE OF BORON 
SLURRIES AND BLENDS OF PENTABORANE IN 
OCTENE-1. Leonard K. Tower. June 1955. 79p. 
diagrs. (NACA RM E55A31) 



ANALYTICAL COMPARISON OF CONVECTION- 
COOLED TURBINE BLADE COOLING- AIR RE- 
QUIREMENTS FOR SEVERAL RADIAL GAS- 
TEMPERATURE PROFILES. James E. Hubbartt 
and Henry O. Slone. September 1955. 46p. diagrs. 
(NACA RM E55G14) 



FACTORS THAT AFFECT OPERATIONAL RELI- 
ABILITY OF TURBOJET ENGINES. Lewis 
Laboratory Staff. January 1956. 376p. diagrs., 
photos., tabs. (NACA RM E55H02) 



EVALUATION OF AN AUTOMATIC INLET- 
PRESSURE CONTROL VALVE FOR STUDY OF 
TRANSIENT ENGINE PERFORMANCE CHARACTER- 
ISTICS. Lewis E. Wallner, Robert J. Lubick, and 
Harry E. Bloomer. April 1956. 25p. diagrs., 
photo. (NACA RM E55L13) 



FABRICATION AND ENDURANCE OF AIR-COOLED 
STRUT -SUPPORTED TURBINE BLADES WITH 
STRUTS CAST OF X-40 ALLOY. Eugene F. Schum, 
Francis S. Stepka, and Robert E. Oldrieve. April 
1956. 39p. diagrs., photos., tabs. 
(NACA RM E56A12) 



ANALYTIC EVALUATION OF EFFECT OF INLET- 
AIR TEMPERATURE AND COMBUSTION PRESSURE 
ON COMBUSTION PERFORMANCE OF BORON 
SLURRIES AND BLENDS OF PENTABORANE IN 
OCTENE-1. SUPPLEMENT I - INFLUENCE OF 
NEW BORIC-OXIDE VAPOR-PRESSURE DATA ON 
CALCULATED PERFORMANCE OF PENTABORANE. 
Leonard K, Tower. May 1956. lip. diagrs. 
(NACARME56D02) 



AERODYNAMIC DESIGN OF AXIAL-FLOW COM- 
PRESSORS. VOLUME I. Compressor and Turbine 
Research Division. Edited by Irving A. Johnsen and 
Roberto. Bullock. August 1956. xii, 4 06 p. diagrs., 
photos., tab. (NACA RM E56B03) 



EFFECT OF DESIGN OVER-ALL COMPRESSOR 
PRESSURE RATIO DIVISION ON ACCELERATION 
CHARACTERISTICS OF THREE HYPOTHETICAL 
TWO-SPOOL TURBOJET ENGINES. Richard E. 
Filippi and James F. Dugan, Jr. August 1956. 26p. 
diagrs. (NACA RM E56D13) 



METHODS FOR CALCULATING THRUST AUGMEN- 
TATION AND LIQUID CONSUMPTION FOR VARIOUS 
TURBOJET -AFTERBURNER FUELS. James F. 
Morris. October 1956. 73p. diagrs. 
(NACARM E56A23) 



PERFORMANCE OF IN CON EL 739 BUCKETS IN 
J33-9 TURBOJET ENGINE. C. A. Gyorgak and 
J. R. Johnston. October 1956. 19p. diagrs., 
photos., tabs. (NACA RM E56E24) 



ANALYSIS OF TURBOJET-ENGINE CONTROLS FOR 
AFTERBURNER STARTING. W. E. Phillips, Jr. 
October 1956. 61p. diagrs., tabs. 
(NACA RM E56F29) 



NEAR NOISE FIELD OF A JET-ENGINE EXHAUST. 
Walton L. Howes, Edmund E. Callaghan, Willard D. 
Coles, and Harold R. Mull. Appendix B: CORRE- 
LATION COMPUTER. ChannlngC. Conger and 
Donald F. Berg. 1957. ii, 35p. diagrs., photos., 
tab. (NACA Rept. 1338, Supersedes TN 3763 and 
TN 3764) 



INVESTIGATION OF 70 PERCENT TRIMETHYL 
BORATE - 30 PERCENT METHYL ALCOHOL FUEL 
MIXTURE IN A SINGLE J33 COMBUSTOR AND IN A 
J33 TURBOJET ENGINE. Louis J. Schafer, Jr., 
and Robert O. Hickel. January 1957. 26p. diagrs., 
photos., tab. (NACA RM E53C24) 



(3) PROPULSION 



197 



A STUDY OF LIQUID BORIC OXIDE PARTICLE 
GROWTH RATES IN A GAS STREAM FROM A SIM- 
ULATED JET ENGINE COMBUSTOR. Paul C. 
Setze, April 1957. 41p. diagrs.. photos., tab. 
(NACA RM E55I20a) 



EXPERIMENTAL INVESTIGATION OF MODIFIED 
CAST-CORED BLADES HAVING HOLLOW TIP 
SECTIONS. Robert E. Oldrieve and John C. 
Free he. June 1957. 36p. diagrs. t photos., 
(NACA RM E57C15) 



SCREEN-TYPE NOISE REDUCTION DEVICES FOR 
GROUND RUNNING OF TURBOJET ENGINES. 
Wlllard D. Coles and Warren J. North. July 1957. 
23p. diagrs., photos. (NACA TN 4033) 



DETERMINATION OF SURGE AND STALL LIMITS 
OF AN AXIAL- FLOW TURBOJET ENGINE FOR 
CONTROL APPLICATIONS. Ross D. Schmidt, 
George Vasu, and Edward W, McGraw. September 
1957. 29p. diagrs., tab. (NACA TN 3585. 
Supersedes RM E53B10) 



CALCULATED AND MEASURED STRESSES IN SIM- 
PLE PANELS SUBJECT TO INTENSE RANDOM 
ACOUSTIC LOADING INCLUDING THE NEAR NOISE 
FIELD OF A TURBOJET ENGINE. Leslie W. 
Lassiter and Robert W. Hess. September 1957. 
33p. diagrs. (NACA TN 4076) 



EFFECT OF DJ1TIAL MTXTURE -TEMPERATURE ON 
BURNING VELOCITY OF HYDROGEN-AIR MIX- 
TURES WITH PREHEATING AND SIMULATED 
PREBURNTNG . Sheldon Heimel. October 1957. 
23p. diagrs., tabs. (NACA TN 4156) 



EXPERIMENTAL INVESTIGATION OF TURBOJET- 
ENGINE MULTIPLE-LOOP CONTROLS FOR NON- 
AFTERBURNING AND AFTERBURNING MODES OF 
ENGINE OPERATION. Donald B. Kirsch, Leon M. 
Wenzel, and Clint E. Hart. January 1958. Qlp. 
diagrs., tab. (NACA TN 4159) 



THEORETICAL INVESTIGATION OF SUBSONIC 
OSCILLATORY BLADE-ROW AERODYNAMICS. 

Frank Lane and Manfred Friedman, New York 
University. February 1958. 64 p. diagrs., tabs. 
(NACA TN 4136) 



APPLICATION OF A HIGH-TEMPERATURE STATIC 
STRAIN GAGE TO THE MEASUREMENT OF THER- 
MAL STRESSES IN A TURBINE STATOR VANE. 
R. H. Kemp, C. R. Morse, and M. H. Hirschberg. 
March 1958. 36p. diagrs., photos., tab. 
(NACA TN 4215) 



EFFKCT OF PRIOR AIR FORCE OVERT EMPERA- 
TURE OPERATION ON LIFE OF J47 BUCKETS 
EVALUATED IN A SEA-LEVEL CYCLIC ENGINE 
TEST. Robert A. Signorelli, James R. Johnston, 
and Floyd B. Garrett. April 1958. 41p. diagrs., 
photos., tabs. (NACA TN 4263) 



/IBRATION SURVEY OF FOUR REPRESENTATIVE 
TYPES OF AIR-COOLED TURBINE BLADES. 
Howard F. Calvert and Gordon T. Smith. July 1958. 
22p. diagrs., photos., tabs. (NACA TN 4100) ~ 



THEORETICAL AND EXPERIMENTAL ANALYSIS OF 
THE REDUCTION OF ROTOR BLADE VIBRATION IN 
TURBOMACHINERY THROUGH THE USE OF MODI- 
FIED STATOR VANE SPACING. Richard H. Kemp, 
Marvin H. Hirschberg, and William C. Morgan 
September 1958. 43p. diagrs., photos., tabs. 
(NACA TN 4373) 



(3.1.4) 
TURBO-PROPELLER ENGINES 



TURBINE DESIGN CONSIDERATIONS FOR 
TURBINE-PROPELLER ENGINE OPERATING OVER 
A RANGE OF FLIGHT CONDITIONS. Elmer H. 
Davison. June 1953. 20p. diagrs., tab. 
(NACA RM E53D16) 



ALTITUDE PERFORMANCE AND OPERATIONAL 
CHARACTERISTICS OF AN XT38-A-2 TURBOPROP 
ENGINE. R. H. Essig and F. W. Schulze. March 
1954. 43p. diagrs., photos., tab. (NACA 
RM E53L18a) 



TURBOPROP-ENGINE DESIGN CONSIDERATIONS. 
I - EFFECT OF MODE OF ENGINE OPERATION ON 
PERFORMANCE OF TURBOPROP ENGINE WITH 
CURRENT COMPRESSOR PRESSURE RATIO. 
Elmer H. Davison. May 1955. 34p. diagrs. 
(NACARME54D19) 



TURBOPROP-ENGINE DESIGN CONSIDERATIONS. 
H - DESIGN REQUIREMENTS AND PERFORMANCE 
OF TURBOPROP ENGINES WITH A SINGLE-SPOOL 
HIGH-PRESSURE-RATIO COMPRESSOR. Elmer H. 
Davison and Margaret C. Stalla. May 1955. 32p. 
diagrs., tabs. (NACA RM E55B18) 



ANALYTICAL AND EXPERIMENTAL STUDY OF 
TRANSIENT-RESPONSE CHARACTERISTICS OF A 
TURBOPROP ENGINE. R. T. Craig, S. Nakanlshl, 
and D. B. Wile. October 1955. 5 Op. diagrs., photo., 
tabs. (NACA RM E55C23) 



AERODYNAMIC DESIGN OF AXlAL-FLOW COM- 
PRESSORS. VOLUME I. Compressor and Turbine 
Research Division. Edited by Irving A. Johnsen and 
Robert O. Bullock. August 1956. xii, 4 06 p. diagrs., 
photos., tab. (NACA RM E56B03) 



NOISE SURVEY OF A FULL-SCALE SUPERSONIC 
TURBINE-DRIVEN PROPELLER UNDER STATIC 
CONDITIONS. Max C. Kurbjun. July 1957 20p. 
diagrs., photo., tab. (NACA TN 4059) 



NOISE SURVEY UNDER STATIC CONDITIONS OF A 
TURBINE-DRIVEN FULL-SCALE MODIFIED 
SUPERSONIC PROPELLER WITH AN ADVANCE 
RATIO OF 3.2. Max C. Kurbjun. January 1958. 
17p. diagrs., photo., tabs. (NACA TN 4172) r 



THEORETICAL AND EXPERIMENTAL ANALYSIS OF 
THE REDUCTION OF ROTOR BLADE VIBRATION IN 
TURBOMACHINERY THROUGH THE USE OF MODI- 
FIED STATOR VANE SPACING- Richard H. Kemp, 
Marvin H. Hirschberg, and William C. Morgan. 
September 1958. 43p. diagrs., photos., tabs- 
(NACA TN 4373) 



198, 



(3) PROPULSION 



(3.1.7) 
RAM- JET ENGINES 



INVESTIGATION OF EFFECTS OF SEVERAL FUEL- 
INJECTION LOCATIONS ON OPERATIONAL PER- 
FORMANCE OF A 20-INCH RAM JET. W. H. 
Sterbentz, E. Perchonok, and F. A. Wilcox. 
June 8, 1948. 39p. diagrs., photos.. 
(NACA RM E7L02) 



INVESTIGATION OF COMBUSTION IN 16 -INCH RAM 
JET UNDER SIMULATED CONDITIONS OF HIGH 
ALTITUDE AND HIGH MACH NUMBER. T. J. 
Nussdorfer, D. C. Sederstrom, andB. Perchonok. 
June 27, 1950. 53p. diagrs., photos., tabs. 
(NACARM E50D04^ 



ALTITUDE-TEST-CHAMBER INVESTIGATION OF 
PERFORMANCE OF A 28-INCH RAM -JET ENQINE. 
I - COMBUST* ION AND OPERATIONAL PERFORM- 
ANCE OF FOUR COMBUSTION- CHAMBER CONFIG- 
URATIONS. W. L. Jones, T. B. Shillito, and J. G. 
Henzel, Jr. August 23, 1950. 53p. diagrs., photos. 
(NACA RM E50F16) 



ALTITUDE-TEST-CHAMBER INVESTIGATION OF 
PERFORMANCE OF A 28-INCH RAM -JET ENGINE. 
II - EFFECTS OF GUTTER WIDTH AND BLOCKED 
AREA ON OPERATING RANGE AND COMBUSTION 
EFFICIENCY. T. B. Shillito, W. L. Jones, and 
R. W. Kahn. November 6, 1950. 58p. diagrs. 
(NACA RM E50H21) 



ALTITUDE-TEST-CHAMBER INVESTIGATION OF 
PERFORMANCE OF A 28-INCH RAM -JET ENGINE. 
IH - COMBUSTION AND OPERATIONAL PERFORM- 
ANCE OF THREE FLAME HOLDERS WITH A CEN- 
TER PILOT BURNER. Thomas B. Shillito, George 
G. Younger, and James G. Henzel, Jr. February 6, 
1951. 30p. diagrs. (NACA RM E5OJ20) 



FORCE AND PRESSURE CHARACTERISTICS FOR A 
SERIES OF NOSE INLETS AT MACH NUMBERS 
FROM 1.59 TO 1.99. H - ISENTROPIC -SPIKE ALL- 
EXTERNAL COMPRESSION INLET. L. J. Obery 
andG. W. Englert. February 9, 1951. 67p. 
diagrs., photos., tabs. (NACA RM E50J26a) 



FORCE AND PRESSURE CHARACTERISTICS FOR A 
SERIES OF NOSE INLETS AT MACH NUMBERS 
FROM 1.59 TO 1 .99 . m - CONICAL-SPIKE ALL- 
EXTERNAL -COMPRESSION INLET WITH SUPER- 
SONIC COWL UP. Maynard I. Weinstein and Joseph 
Davids. February 14, 1951. 51p. diagrs., tabs. 
(NACA RM E50J30) 



FLIGHT PERFORMANCE OF A TWIN-ENGINE 
SUPERSONIC RAM JET FROM 2,300 TO 
67,200 FEET ALTITUDE. H. Rudolph Dettwyler 
and Aleck C. Bond. February 19, 1951. 23p. 
diagrs., photos., tab. (NACA RM L50L27) 



INTERNAL FLOW AND BURNING CHARACTERIS- 
TICS OF 16-INCH RAM JET OPERATING IN A FREE 
JET AT MACH NUMBERS OF 1.35 AND 1.73. 
Eugene Perchonok and John M. Farley. May 21, 
1951. 37p. dLigrs., photos., tab. 
(NACA RM E51C16) 



ALTITUDE -TEST-CHAMBER INVESTIGATION OF 
PERFORMANCE OF A 28-INCH RAM -JET ENGINE. 
IV - EFFECT OF INLET-AIR TEMPERATURE, 
COMBUSTION-CHAMBER-INLET MACH NUMBER, 
AND FUEL VOLATILITY ON COMBUSTION PER- 
FORMANCE. Robert W. Kahn, Shigeo Nakanishi, 
and James L. Harp, Jr. July 1951. 27p. diagrs. 
(NACA RM E51D11) 



EFFECT OF FUEL DENSITY AND HEATING VALUE 
ON RAM-JET AIRPLANE RANGE. Hugh M. 
Henneberry. February 1952. 56p. diagrs., tabs. 
(NACA RM E51L21) 



TRANSONIC FREE-FLIGHT DRAG RESULTS OF 
FULL-SCALE MODELS OF 16-INCH-DIAMETER 
RAM -JET ENGINES. Wesley E. Messing and 
LorenW. Acker. April 1952. 17p. diagrs 
(NACARME52B19) 



EVALUATION OF FIVE CONICAL CENTER-BODY 
SUPERSONIC DIFFUSERS AT SEVERAL ANGLES OF 
ATTACK. Gerald W. Englert and Leonard J. Obery. 
May 1952. 29p. diagrs., photos., tab. 
(NACARME51L04) 



TRANSONIC FREE-FLIGHT INVESTIGATION OF THE 
TOTAL DRAG AND OF THE COMPONENT DRAGS 
(COWL PRESSURE, ADDITIVE, BASE, FRICTION, 
AND INTERNAL) ENCOUNTERED BY A 16-INCH- 
DIAMETER RAM -JET ENGINE FOR MACH NUMBERS 
FROM 0.80 TO 1 .43 . Wesley E . Messing and 
Leonard Rabb. August 1952. 34p. diagrs., photos. 
(NACA RM E52F02) 



SPREADING OF EXHAUST JET FROM 16-INCH RAM 
JET AT MACH NUMBER 2.0. Fred Wilcox and 
Donald Pennington. August 1952. 14p. diagrs.. 
photo., tab. (NACA RM E52F25) 



PERFORMANCE CHARACTERISTICS OF CANARD- 
TYPE MISSILE tfTCTH VERTICALLY MOUNTED 
NACELLE ENGINES AT MACH NUMBERS 1.5 TO 
2.0. Leonard J. Obery and Howard S. Krasnow. 
September 1952. 25 p. diagrs. (NACA RM E52H08) 



PERFORMANCE CHARACTERISTICS OF CANARD- 
TYPE MISSDLE WITH WING-MOUNTED NACELLE 
ENGINES AT MACH NUMBERS 1 .5 TO 2.0. Emll J. 
Kremzier and Joseph Davids. November 1952. 
30p. diagrs., tab. (NACA RM E52J08) 



EFFECT OF FUEL-AIR RATIO CONCENTRATION 
IN COMBUSTION ZONE ON COMBUSTION PER- 
FORMANCE OF A 16-INCH RAM-JET ENGINE. 
A. J. Cervenka, D. W. Bahr, andE.E. Dangle. 
April 1953. 24p. diagrs., tab. 
(NACA RM E53B19) 



FREE-JET ALTITUDE INVESTIGATION OF A 20- 
INCH RAM -JET COMBUSTOR WITH A RICH INNER 
ZONE OF COMBUSTION FOR rMPROVED LOW- 
TEMPERATURE-RATIO OPERATION. Arthur M. 
Trout and Carl B. Wentworth. May 1953. 28o. 
diagrs., photo. (NACA RM E52L26) 



EFFECT OF FUEL INJECTOR LOCATION AND 
MTXTURE CONTROL ON PERFORMANCE OF A 
16-INCH RAM-JET CAN-TYPE COMBUSTOR. 
A. J. Cervenka, Eugene Perchonok, and E. E. 
Dangle. July 1953. 33p. diagrs., tab. (NACA 
RM E53F15) 



(3) PROPULSION 



199 



ENGINEERING METHOD OF RAM-JET THRUST 
DETERMINATION BASEP ON EXPERIMENTALLY 
OBTAINED COMBUSTOR PARAMETERS. 
H. Rudolph Dettwyier and Maxime A. Paget. August 
1953. 44p. diagrs., tab. (NACA RM L53E21) 



EFFECT OF INLET-AIR TEMPERATURE ON PER- 
FORMANCE OF A 16 -INCH RAM- JET COMBUSTOR. 
A. J. Cervenka, E. E. Dangle, and Robert 
Friedman. October 1953. 24p. diagrs., tab. 
(NACA RM E53I03* 



INVESTIGATION OF CONICAL SUBSONIC DIFFUS- 
ERS FOR RAM-JET ENGINES. John M. Farley and 
Henry J. We In a. March 1954. 40p. diagrs., 
photos., tabs. (NACA RM E53L15) 



INVESTIGATION OF A TRANSLATING -CONE INLET 
AT MACH NUMBERS FROM 1.5 TO 2.0. L. Abbott 
Leissler and William H. Sterbentz. May 1954. 29p. 
diagrs., photos., tab. (NACA RM E54B23) 



EFFECT OF MECHANICALLY INDUCED SINUSOIDAL 
AIR-FLOW OSCILLATIONS ON OPERATION OF A 
RAM -JET ENGINE. E. E. Dangle, A. J. Cervenka, 
and Eugene Perchonok. June 1954. 24p. diagrs., 
tab. (NACA'RM E54D01) 



PERFORMANCE OF A 15-INCH RAM-JET ENGINE 
WITH A CAN-TYPE COMBUSTOR AT MACH NUM- 
BERS OF 1.50 TO 2.16. Donald P. Hearth and 
Eugene Perchonok. August 1954. 30p. diagrs. 
(NACA RM E54G13) 



DRAG DATA FOR 16-INCH-DIAMETER RAM-JET 
ENGINE WITH DOUBLE-CONE INLET IN FREE 
FLIGHT AT MACH NUMBERS FROM 0.7 TO 1.8. 
Merle L. Jones, Leonard Rabb, and Scott H. 
Simpkinson. October 1954. 52p. diagrs., photos. 
(NACA RM E54H02) 



FLIGHT AND PREFLIGHT TESTS OF A RAM JET 
BURNING MAGNESIUM SLURRY FUEL AND 
UTILIZING A SOLID-PROP ELLANT GAS GENERA- 
TOR FOR FUEL EXPULSION. Walter A. Bartlett, 
Jr., and William K. Hagginbothom, Jr. Apr" 1955. 
35p. diagrs., photos. (NACA RM L55A34) 



ANALYTIC EVALUATION OF EFFECT OF INLET- 
AIR TEMPERATURE AND COMBUSTION PRESSURE 
ON COMBUSTION PERFORMANCE OF BORON 
SLURRIES AND BLENDS OF PENTABORANE IN 
OCTENE-1. Leonard K. Tower. June 1955. 79p. 
diagrs. (NACA RM E55A31) 



AN ANALYSIS OF RAM-JET -ENGINE TIME DELAY 
FOLLOWING A FUEL-FLOW DISTURBANCE. 
Fred A. Wilcox and Arthur R. Anderson. June 1955. 
38p. diagrs., tabs. (NACA RM E55D22) 



ANALYTIC EVALUATION OF EFFECT OF INLET- 
AIR TEMPERATURE AND COMBUSTION PRESSURE 
ON COMBUSTION PERFORMANCE OF BORON 
SLURRIES AND BLENDS OF PENTABORANE IN 
OCTENE-1. SUPPLEMENT I - INFLUENCE OF 
NEW BORIC-OXIDE VAPOR-PRESSURE DATA ON 
CALCULATED PERFORMANCE OF PENTABORANE. 
Leonard K. Tower. May 1956. lip. diagrs. 
(NACA PM E56D02) 



PREFLIGHT AND FLIGHT-TEST INVESTIGATION 
OF A 50-PERCENT-MAGNESIUM 50-PERCENT 
JP-4 SLURRY FUEL IN A TWIN-ENGINE RAM-JET 
VEHICLE. Otto F. Trout, Jr., and Thomas L. 
Kennedy. May 1956. 27p. diagrs., photos. 
(NACA RM L56C06) 



FLIGHT INVESTIGATION OF A RAM JET BURNING 
MAGNESIUM SLURRY FUEL AND HAVING A CONI- 
CAL SHOCK INLET DESIGNED FOR A MACH NUM- 
BER OF 4.1. Walter A. Bartlett, Jr., and 
Charles F. Merlet. January 1957. 23p. diagrs., 
photos. (NACA RM L56I24a) 



A STUDY OF LIQUID BORIC OXIDE PARTICLE 
GROWTH RATES IN A GAS STREAM FROM A SIM- 
ULATED JET ENGINE COMBUSTOR. Paul C. 
Setze. April 1957. 41p. diagrs., photos., tab. 
(NACA RM E55I20a) 



DROP -SIZE DISTRIBUTION FOR CROSSCURRENT 
BREAKUP OF LIQUID JETS IN A1RSTREAMS. 
Robert D. Ingebo and Hampton H. Foster. 
October 1957. 36p. diagrs., photos, tabs. 
(NACA TN 4087) 



STUDY OF SOME BURNER CROSS-SECTION 
CHANGES THAT INCREASE SPACE-HEATING 
RATES. Donald R. Boldman and Perry L. 
Blacfcshear, Jr. November 1957. 38p. diagrs., 
photos., tab. (NACA TN 4162) 



EXTREME SPEEDS AND THERMODYNAMIC 
STATES IN SUPERSONIC FLIGHT. (Extreme 
Geschwindigkeiten und therm is che Zustande beim 
Uberschallflug. ) Klaus Oswatitsch. April 1958. 
39p. diagrs., tabs. (NACA TM 1434. Translation 
from Zeitschrift fur Flugwlssenschaften, v. 4, 
no. 3/4, 1956, p. 95-108) 



PRELIMINARY SURVEY OF PROPULSION USING 
CHEMICAL ENERGY STORED IS THE UPPER 
ATMOSPHERE. Lionel V. Baldwin and Perry L. 
Blackshear. Appendix D: HEAT TRANSFER AND 
FRICTION DRAG. James F. Schmidt. May 1958. 
73p. diagrs., tabs. (NACA TN 4267) 



AN ANALYSIS OF RAMJET ENGINES USING SUPER- 
SONIC COMBUSTION. Richard J. Weber and John 
S. Mac Kay. September 1958. 49p. diagrs., tab. 
(NACA TN 4386) 



(3.1.8) 
ROCKET ENGINES 



PRELIMINARY INVESTIGATION OF A CHEMICAL 
STARTING TECHNIQUE FOR THE ACID GASOLINE 
ROCKET PROPELLANT SYSTEM. Glen Hennings 
and Gerald Morrell. January 1953. 23p. photo., 
diagrs., tab. (NACA RM E52K21) 



INVESTIGATION OF LIQUID FLUORINE - LIQUID 
AMMONIA PROPELLANT COMBINATION IN A 100- 
POUND-THRUST ROCKET ENGINE. Edward A., 
Rothenberg and Howard W. Douglass. July 1953. 
31p. diagrs., photos., tabs. (NACA RM E53E08) 



200 



(3) PROPULSION 



ROCKET-POWERED MODEL INVESTIGATION OF 
LIFT, DRAG, AND STABILITY OF A BODY -TAIL 
CONFIGURATION AT MACH NUMBERS FROM 0.8 
TO 2.3 AND ANGLES OF ATTACK BETWEEN t6.5*. 
Warren Gillespie, Jr., and Albert E. Dietz. April 
1954. 42p. diagrs., photos., tabs. 
(NACA RM L54C04) 



PHOTOGRAPHIC STUDY OF ROTARY SCREAMING 
AND OTHER OSCILLATIONS IN A ROCKET ENGINE. 
Theodore Male, William R. Kerslake, and 
AdelbertO. Tischler. May 1954. 37p. diagrs., 
photos. (NACA RM E54A29) 



THEORETICAL PERFORMANCE OF JP-4 FUEL 
WITH A 70-PERCENT-FLUORINE - 30-PERCENT - 
OXYGEN MIXTURE AS A ROCKET PROPELLANT. 
I - FROZEN COMPOSITION. Sanford Gordon and 
VearlN. Huff. April 1956. 38p. diagrs., tabs. 
(NACA RM E56A13a) 



EFFECT OF FUELS ON SCREAMING IN 200- 
POUND-THRUST LIQUID-OXYGEN - FUEL ROCKET 
ENGINE. Isaac Pass and Adelbert O. Tischler. 
June 1956. 25p. diagrs., photos., tab. 
(NACA RM E56C10) 



INJECTION PRINCIPLES FOR LIQUID OXYGEN AND 
HEPTANE USING TWO-ELEMENT INJECTORS. 
Marcus F. Heidmann. June 1956. 30p. diagrs., 
photos., tab. (NACA RM E56D04) 



A BRIEF SUMMARY OF EXPERIENCE IN BOOSTING 
AERODYNAMIC RESEARCH MODELS. Joseph G. 
Thibodaux, Jr. (Report is basis of talk presented 
at the thirtieth meeting of Bumblebee Aerodynamics 
Panel, Buffalo, New York, January 4, 1956.) July 
1956. 21p. diagrs., photos. (NACA RM L56E28) 



THEORETICAL PERFORMANCE OF JP-4 FUEL 
WITH A 70-30 MIXTURE OF FLUORINE AND 
OXYGEN AS A ROCKET PROPELLANT. H - EQUI- 
LIBRIUM COMPOSITION. Sanford Gordon and Vearl 
N. Huff. October 1956. 49p. diagrs., tabs. 
(NACARME56F04) 



EFFECTS OF VARIATIONS IN COMBUSTION - 
CHAMBER CONFIGURATION ON IGNITION DELAY 
IN A 50-POUND-THRUST ROCKET. Dezso J." 
Ladanyi. October 1956. 53p. diagrs., photos., tabs. 
(NACA RM E56F22) 



A STUDY OF INJECTION PROCESSES FOR LIQUID 
OXYGEN AND GASEOUS HYDROGEN IN A- 200- 
POUND-THRUST ROCKET ENGINE. Carmon M. 
Auble. January 1957. 32p. diagrs., photos. 
(NACARM E56125^ 



REACTION OF FLUORINE WITH CARBON AS A 
MEANS OF FLUORINE DISPOSAL. Harold W. 
Schmidt. July 1957. 17p. diagrs., tab. 
(NACARME57E02) 



PROPELLANT VAPORIZATION AS A CRITERION 
FOR ROCKET-ENGINE DESIGN; EXPERIMENTAL 
EFFECT OF FUEL TEMPERATURE ON UQUHD- 
OXYGEN - HEPTANE PERFORMANCE. M. F. 
Heidmann. July 1957. 21p. diagrs., tabs. 
(NACA RM E57E03) 



INJECTION PRINCIPLES FOR LIQUID OXYGEN AND 
HEPTANE USING NINE-ELEMENT INJECTORS IN 
AN 1800-POUND -THRUST ROCKET ENGINE. 
Richard F. Neu. July 1957. 27p. diagrs., photos., 
tab. (NACA RM E57E13) 



PROPELLANT VAPORIZATION AS A CRITERION 
FOR ROCKET ENGINE DESIGN; CALCULATIONS 
OF CHAMBER LENGTH TO VAPORIZE A SINGLE 
n-HEPTANE DROP. Richard J. Prlem. July 1957. 
41p. diagrs., tab. (NACA TN 3985) 



ANALYSIS OF TWO-STAGE-TURBINE EFFICIENCY 
CHARACTERISTICS IN TERMS OF WORK AND 
SPEED REQUIREMENTS. Warner L. Stewart and 
William T. Wintucky. August 1957. 45p. diagrs., 
tabs. (NACA RM E57F12) 



EFFECT OF FLUID-SYSTEM PARAMETERS ON 
STARTING FLOW IN A LIQUID ROCKET. 
Richard P. Krebs. September 1957. 38p. diagrs., 
tab. (NACA TN 4034) 



PROPELLANT VAPORIZATION AS A CRITERION 
FOR ROCKET -ENGINE DESIGN; CALCULATIONS 
USING VARIOUS LOG -PROBABILITY DISTRTOUt 
TIONS OF HEPTANE DROPS. Richard J. Priem. 
October 1957. 29p. diagrs., tab. (NACA TN 4098) 



THEORETICAL ROCKET PERFORMANCE OF 
JP-4 FUEL WITH.SEVERAL FLUORINE-OXYGEN 
MDCTURES ASSUMING FROZEN COMPOSITION. 
Sanford Gordon and Kenneth 3. Drellishak. 
November 1957. 62p. diagrs. , tabs. 
(NACA RM E57G16a) 



EFFECT OF FUEL-ORIFICE DIAMETER ON PER- 
FORMANCE OF HEPTANE-OXYGEN ROCKET 
> ENGINES . Richard J . Priem and Martin Hersch 
February 1958. 20p. diagrs. (NACA RM E57I26) 



THEORETICAL ROCKET PERFORMANCE OF JP-4 
FUEL WITH SEVERAL FLUORINE -OXYGEN MIX- 
TURES ASSUMING EQUILIBRIUM COMPOSITION. 
Sanford Gordon. February 1958. 69p. diagrs., 
tabs. (NACA RM E57K22) 



FRICTION STUDIES OF VARIOUS MATERIALS IN 
LIQUID NITROGEN. D. W. Wisander, W. F. Hady, 
and R. L. Johnson. February 1958. 35p. diagrs., 
photos., tab. (NACA TN 4211) 



PROPELLANT VAPORIZATION AS A CRITERION 
FOR ROCKET ENGINE DESIGN; RELATION BE- 
TWEEN PERCENTAGE OF PROPELLANT VAPOR- 
IZED AND ENGINE PERFORMANCE. Marcus F. 
Heidmann and Richard J. Priem. March 1958. 
19p. diagrs. (NACA TN 4219) 



DROP -SIZE DISTRIBUTIONS FOR1MPINGING-JET 
BREAKUP IN AIRSTREAMS SIMULATING THE 
VELOCITY CONDITIONS IN ROCKET COMBUSTORS. 
Robert D. Ingebo. March 1958. 23p. diagrs. 
photos., tab. (NACA TN 4222) 



(3) PROPULSION 



201 



EXTREME SPEEDS AND THERMODYNAMIC 
STATES IN SUPERSONIC FLIGHT. (Extreme 
Gesrhwindigkeiten und thermische Zustande beim 
Uberschallflug.) Klaus Oswatitsch. April 1958. 
39p. diagrs., tabs. (NACA TM 1434. Translation 
from Zeitschrift fur Flugwissenschaften, v. 4, 
no. 3/4, 1956 ; p. 95-108) 



THEORETICAL PERFORMANCE OF LIQUID AMMO- 
NIA WITH LIQUID OXYGEN AS A ROCKET PROPEL- 
LANT. Sanford Gordon and Alan R. Glueck. May 
1958. 84p. diagrs.. tabs. (NACA RM E58A21) 



THEORETICAL ROCKET PERFORMANCE OF 
LIQUID METHANE WITH SEVERAL FLUORINE- 
OXYGEN MDCTURES ASSUMING FROZEN COMPOSI- 
TION. Sanford Gordon and Michael E. Kastner. 
May 1958. 44p. diagrs., tabs. (NACA RM E58B20) 



EFFECT OF FUEL DROP SIZE AND INJECTOR 
CONFIGURATION ON SCREAMING IN A 200-POUND- 
THRUST ROCKET ENGINE USING LIQUID OXYGEN 
AND HEPTANE. Charles E. Feiler. June 1958. 
27p. diagrs., photos., tab. (NACA RM E58A20a) 



SCREAMING TENDENCY OF THE GASEOUS- 
HYDROGEN - LIQUID-OXYGEN PROPELLANT 
COMBINATION, iouis Baker, Jr., and Fred W. 
Steffen. September 1958. 24p. diagrs., photos., 
tabs. (NACA RM E58E09} 



COMBUSTOR PERFORMANCE WITH VARIOUS 
HYDROGEN-OXYGEN INJECTION METHODS IN A 
200-POUND-THRUST ROCKET ENGINE. M. F. 
Heidmann and Louis Baker, Jr. September 1958. 
45p. diagrs., photos., tab. (NACA RM E58E21) 



PROPELLANT VAPORIZATION AS A CRITERION 
FOR ROCKET-ENGINE DESIGN; CALCULATIONS 
OF CHAMBER LENGTH TO VAPORIZE VARIOUS 
PROPELLANTS. Richard J. Priem. September 
1958. 36p. diagrs., tab. (NACA TN 3883) 



A MACH 4 ROCKET-POWERED SUPERSONIC TUN- 
NEL USING AMMONIA -OXYGEN AS WORKING 
FLUID. Robert W. Graham, Eleanor Costilow 
Guentert, and Vearl N. Huff. September 1958. 53p. 
diagrs., photos. (NACA TN 4325) 



RELATIVE MOTION IN THE TERMINAL PHASE OF 
INTERCEPTION OF A SATELLITE OR A BALLISTIC 
MISSILE. Richard A. Hord. September 1958. 33p. 
diagrs.. tab. (NACA TN 4399) 



(3.1.9) 
JET- DRIVEN ROTORS 



ANALYSIS OF A PRESSURE-JET POWER PLANT 
FOR A HELICOPTER. Richard P. Krebs and 
Williams. Miller, Jr. March 1955. 56p. diagrs. 
(NACA RM E54L23) 



EFFECT OF AMBIENT CONDITIONS ON THE PER- 
FORMANCE OF A PRESSURE-JET POWERPLANT 
FOR A HELICOPTER. Richard P. Krebs. June 
1956. 49p. diagrs. (NACA RM E56B21) 



EXPLORATORY INVESTIGATION OF A HELICOP- 
TER PRESSURE-JET SYSTEM ON THE LANGLEY 
HELICOPTER TEST TOWER. Robert A. Makofski 
and James P. Shivers. July 1956. 38p. diagrs., 
photo. (NACA RM L56B17) 



ON PAIRS OF SOLUTIONS OF A CLASS OF INTER- 
NAL VISCOUS FLOW PROBLEMS WITH BODY 
FORCES. Simon Ostrach and Lynn U. Albers. 
June 1958. 21p. diagrs., tabs. (NACA TN 4273) 



(3.1.10) 
NUCLEAR-ENERGY SYSTEMS 



DISTRIBUTION OF FISSIONABLE MATERIAL IN 
THERMAL REACTORS OF SPHERICAL GEOMETRY 
FOR UNIFORM POWER GENERATION. Robert R. 
McCready, Robert B. Spooner, and Michael F. 
Valerino. June 1952. 36p. diagrs., tab. 
(NACA RM E52C11) 



CALCULATION OF INTERNAL PRESSURES IN THE 
FUEL TUBE OF A NUCLEAR REACTOR. B. M. 

Rosenbaum and G. Allen. July 1952. 32p. tabs. 
(NACA RM E52B28) 



EFFECT OF CAPTURE ON THF, ST .OWING -DOWN 
LENGTH OF NEUTRONS IN HYDROGENOUS 
MIXTURES CONTAINING URANIUM. H. C. Volkin 
and L. Soffer. April 1953. 4p. tab. 
(NACA RME53B05) 



COMPARISON OF CALCULATED AND MEASURED 
THERMAL DISTORTIONS IN A REACTOR CONTROL 
ROD FOR TEMPERATURE PATTERNS SIMULATING 
TWO REACTOR OPERATING CONDITIONS. Tibor F. 
Nagey. April 1953. 18p. diagrs., tabs. 
(NACA RM E53B26) 



FORCED-CONVECTION HEAT-TRANSFER CHARAC- 
TERISTICS OF MQLTEN^FLINAK FLOWING IN AN 
INCONEL X SYSTEM. Milton D. Grele and Louis 
Gedeon. February 1954. 23p. diagrs., photos., 
tab. (NACA RM E53L18) 



TRANSPORT OF RADIOACTIVITY BY LIQUID 
SODIUM IN A STAINLESS STEEL CIRCULATION 
SYSTEM. D. Fieno and D. Bogart. March 2, 
1955. 17p. diagrs., photos., tab. 
(NACA RM E54K03) 



TWO-DIMENSIONAL DIFFUSION THEORY ANALY- 
SIS OF REACTIVITY EFFECTS OF A FUEL- 
PLATE-REMOVAL EXPERIMENT. Edward R. 
Gotsky, James P. Cusick, and Donald Bogart. 
January 1958. 30p. diagrs., photos., tab. 
(NACA TN 4164) 



(3.1.11) 
MISCELLANEOUS ENGINES 



EXPLORATORY INVESTIGATION OF A HELICOP- 
TER PRESSURE-JET SYSTEM ON THE LANGLEY 
HELICOPTER TEST TOWER. Robert A. Makofski 
and James P. Shivers. July 1956. 38p. diagrs., 
photo. (NACA RM L56B17) 



2 02 



- (3) PROPULSION 



EXPLORATORY INVESTIGATION OF AERODYNAM- 
IC EFFECTS OF EXTERNAL COMBUSTION OF 
ALUMINUM BOROHYDRIDE IN AIRSTREAM ADJA- 
CENT TO FLAT PLATE IN MACH 2.46 TUNNEL. 
Robert G. Dorsch, John S. Serafini, and Edward A. 
Fletcher. July 1957. 91p. diagrs., photos., tabs. 
(NACARM E57E16) 



PRELIMINARY SURVEY OF PROPULSION USING 
CHEMICAL ENERGY STORED IN THE UPPER 
ATMOSPHERE. Lionel V. Baldwin and Perry L. 
Blackshear. Appendix D: HEAT TRANSFER AND 
FRICTION DRAG. James F. Schmidt. May 1958. 
73p. diagrs., tabs. (NACA TN 4267) 



(3) PROPULSION 



203 



(3.2) 
Control of Engines 



CHARACTERISTICS OF A HYDRAULIC CONTROL 
DETERMINED FROM TRANSIENT DATA OBTAINED 
WITH A TURBOJET ENGINE AT ALTITUDE. 
George Vasu, William L. Hinde, and R. T. Craig. 
June 1954. 62p. diagrs., photo., tab. 
(NACA RM E53D02) 



SUMMARY OF SCALE -MODEL THRUST- RE VERSER 
INVESTIGATION. John H. Povolny, Fred W. Steffen, 
and Jack G. McArdle. 1957. ii, 14p. diagrs., 
photos. (NACA Rept. 1314. Supersedes TN 3664) 



(3.2.2) 
CONTROL OF TURBOJET ENGINES 



ALTITUDE STARTING CHARACTERISTICS OF AN 
AFTERBURNER WITH AUTOIGNITBDN AND HOT- 
STREAK IGNITION. P. E. Renas, R. W. Harvey, 
Sr., and E. T. Jansen. April 1953. 25p. diagrs., 
photos., tab. (NACA RM E53B02) 



DYNAMIC CHARACTERISTICS OF A SINGLE - 
SPOOL TURBOJET ENGINE. R. T. Craig, George 
Vasu, and R. D. Schmidt. August 1953. 50p. 
diagrs., tab. (NACA RM E53C17) 



CHARACTERISTICS OF A HYDRAULIC CONTROL 
DETERMINED FROM TRANSIENT DATA OBTAINED 
WITH A TURBOJET ENGINE AT ALTITUDE. 
George Vasu, William L. Hinde, and R. T. Craig. 
June 1954. 62p. diagrs., photo., tab. 
(NACA RM E53D02) 



AN EVALUATION OF TURBOJET ENGINE THRUST 
CONTROL BY EXHAUST-NOZZLE-AREA MODULA- 
TION AND COMPRESSOR-INLET THKOTTLING. 
James L. Harp, Jr., Wallace W. Velie, and William 
E. Mallett. August 1954. 17p. diagrs., photos. 
(NACA RM E54F21) 



EXPERIMENTAL INVESTIGATION OF CONTROL 
SIGNALS AND THE NATURE OF STALL AND SURGE 
BEHAVIOR IN A TURBOJET ENGINE. G. J. Delio 
and P. M. Stiglic. December 1954. 62p. diagrs. 
(NACA RM E54I15) 



INVESTIGATION TO MACH NUMBER 2.0 OF SHOCK- 
POSITIONING CONTROL SYSTEMS FOR A 
VARIABLE-GEOMETRY INLET IN COMBINATION 
WITH A J34 TURBOJET ENGINE. L. Abbott 
Leissler and J. Cary Nettles. December 1954. 19p. 
diagrs. (NACA RM E54I27) 



FACTORS THAT AFFECT OPERATIONAL RELI- 
ABILITY OF TURBOJET ENGINES. Lewis 
Laboratory Staff. January 1956. 376p. diagrs., 
photos., tabs. (NACA RM E55H02) 



AN ANALOG STUDY OF A SHOCK -POSITION D1F- 
FUSER CONTROL ON A SUPERSONIC TURBOJET 
ENGINE. David No vik. August 1956. 27p. diagrs. 
(NACA RM E56E09a) 



ANALYSIS OF TURBOJET -ENGINE CONTROLS FOR 

AFTERBURNER STARTING. W. E. Phillips, Jr. 
October 1956. 61p. diagrs., tabs. 
(NACA RM E56F29) 



DETERMINATION OF SURGE AND STALL LIMITS 
OF AN AXIAL-FLOW TURBOJET ENGINE FOR 
CONTROL APPLICATIONS. Ross D. Schmidt, 
George Vasu, and Edward W. McGraw. September 
1957. 29p. diagrs., tab. (NACA TN 3585. 
Supersedes RM E53L 



ANALYSIS OF SHOCK MOTION IN DUCTS DURING 
DISTURBANCES IN DOWNSTREAM PRESSURE. 
Herbert G. Hurrell. September 1957. Up. diagr. 
(NACA TN 4090) 



EXPERIMENTAL INVESTIGATION OF TURBOJET- 
ENGINE MULTIPLE-LOOP CONTROLS FOR NON- 
AFTERBURNING AND AFTERBURNING MODES OF 
ENGINE OPERATION. Donald B. Kirsch, Leon M. 
Wenzel, and Clint E. Hart. January 1958. 61 p. 
diagrs., tab. (NACA TN 4159) 



(3.2.4) 
CONTROL OF TURBINE- 
ENGINES 



PROPELLER 



ALTITUDE PERFORMANCE AND OPERATIONAL 
CHARACTERISTICS OF AN XT38-A-2 TURBOPROP 
ENGINE. R. H. Essig and F. W. Schulze. March 
1954. 43p. diagrs., photos., tab. (NACA 
RM E53L18a) 



TURBOPROP -ENGINE DESIGN CONSIDERATIONS. 
I - EFFECT OF MODE OF ENGINE OPERATION ON 
PERFORMANCE OF TURBOPROP ENGINE WITH 
CURRENT COMPRESSOR PRESSURE RATIO. 
Elmer H. Davison. May 1955. 34p. diagrs. 
(NACARME54D19) 



TURBOPROP-ENGINE DESIGN CONSIDERATIONS. 
n - DESIGN REQUIREMENTS AND PERFORMANCE 
OF TURBOPROP ENGINES WITH A SINGLE -SPOOL 
HIGH-PRESSURE-RATIO COMPRESSOR. Elmer H. 
Davison and Margaret C. Stalla. May 1955. 32p. 
diagrs., tabs. (NACA RM E55B18) 



ANALYTICAL AND EXPERIMENTAL STUDY OF 
TRANSIENT -RESPONSE CHARACTERISTICS OF A 
TURBOPROP ENGINE. R. T. Craig, S. Nakanishl, 
and D. B. Wile. October 1955. 50p. diagrs., photo., 
tabs. (NACA RM E55C23) 



(3.2.6) 
CONTROL OF RAM 



JET ENGINES 



A PROPOSED RAM-JET CONTROL SYSTEM OPER- 
ATED BY USE OF DIFFUSER PRESSURE RECOV- 
ERY. Maxime A. Faget. September 1352. 19p. 
diagrs. (NACA RM L52E05b) 



204 



(3) PROPULSION 



EFFECT OF MECHANICALLY INDUCED SINUSOIDAL 
AIR-FLOW OSCILLATIONS ON OPERATION OF A 
RAM-JET ENGINE. E. E. Dangle, A. J. Cervenka, 
and Eugene Perchonok. June 1954. 24p. diagrs., 
tab. (NACA RM E54D01) 



AN ANALYSIS OF RAM-JET-ENGINE TIME DELAY 
FOLLOWING A FUEL-FLOW DISTURBANCE. 
Fred A. Wilcox and Arthur R. Anderson. June 1955. 
38p. diagrs., tabs. (NACA RM E55D22) 



ANALYSIS OF SHOCK MOTION IN DUCTS DURING 
DISTURBANCES IN DOWNSTREAM PRESSURE. 
Herbert G. Hurrell. September 1957. lip. diagr. 
(NACA TN 4090) 



(3.2.7) 
CONTROL OF ROCKET ENGINES 

EFFECT OF FLUID-SYSTEM PARAMETERS ON 
STARTING FLOW IN A LIQUID ROCKET. 
Richard P. Krebs. September 1957. 38p. diagrs., 
tab. (NACA TN 4034) 



(3) PROPULSION 



205 



(3.3) 
Auxiliary Booster Systems 



(3.3.2) 
GAS TURBINES 



(3.3.2. 1) 
LIQUID INJECTION 



ANALYTICAL AND EXPERIMENTAL INVESTIGA- 
TION OF THRUST AUGMENTATION OF AXIAL - 
AND CENTRIFUGAL-COMPRESSOR TURBOJET 
ENGINES BY INJECTION OF WATER AND ALCO- 
HOL IN COMBUSTION CHAMBERS. David S. 
Gabriel, Harry W. Dowman, and William L. Jones. 
April 13, 1950. 43p. diagrs., photo. 
(NACA RM E9K29) 



(3.3.2.2) 
AFTERBURNING 



ALTITUDE-WIND-TUNNEL INVESTIGATION OF 
TAIL -PIPE BURNER WITH CONVERGING CONICAL 
BURNER SECTION ON J35-A-5 TURBOJET ENGINE. 
H. Carl Thorman and Carl E. Campbell. 
February 10, 1950. 60p. diagrs., photos., tab. 
(NACA RM E9I16) 



ALTITUDE PERFORMANCE AND OPERATIONAL 
CHARACTERISTICS OF 29-INCH-DIAMETER TAIL- 
PIPE BURNER WITH SEVERAL FUEL SYSTEMS 
AND FUEL-COOLED STAGE-TYPE FLAME 
HOLDERS ON J35-A-5 TURBOJET ENGINE. 
Richard L. Golladay and Harry E. Bloomer. 
April 28, 1950. 57p. diagrs., photos., tab. 
(NACA RM E50A19) 



EXPERIMENTAL INVESTIGATION OF TAIL -PIPE- 
BURNER DESIGN VARIABLES. W. A. Fleming, 
E. William Conrad, and A. W. Young. March 5, 
1951. 75p. diagrs., photos., tab. 
(NACA RM E50K22) 



ALTITUDE PERFORMANCE INVESTIGATION OF 
TWO FLAME-HOLDER AND FUEL-SYSTEM CON- 
FIGURATIONS IN SHORT AFTERBURNER. S . C . 
Huntley and H. D. Wilsted. May 1952. 41p. 
diagrs., photos., tab. (NACA RM E52B25) 



INVESTIGATION OF PERFORMANCE OF SEVERAL 
DOUBLE-SHRCUD EJECTORS AND EFFECT OF 
VARIABLE -AREA EXHAUST NOZZLE ON SINGLE 
EJECTOR PERFORMANCE. C. W. Ellis, D. P. 
Hollister. and H. D. Wilsted. July 1952. 25p. 
diagrs., photos. (NACA RM E52D25) 



EFFECT OF WATER VAPOR ON COMBUSTION OF 
MAGNESIUM -HYDROCARBON SLURRY FUELS IN 
SMALL-SCALE AFTERBURNER. Leonard K. 
Tower. October 1952. 39p. diagrs., tabs. 
(NACA RM E52H25) 



PERFORMANCE OF DOUBLE -SHROUD EJECTOR 
CONFIGURATION WITH PRIMARY PRESSURE 
RATIOS FROM 1.0 TO 10. Donald P. Hollister and 
William K. Greathouse. February 1953. 34p. 
diagrs., tabs. (NACA RM E52K17) 



ANALYSIS OF SEVERAL METHODS OF PUMPING 
COOLING AIR FOR TURBOJET-ENGINE AFTER- 
BURNERS. John C. Samuels and Herbert Yanowltz. 
February 1953. 54p. diagrs. (NACA RM E52Ki'- 



ALTITUDE STARTING CHARACTERISTICS OF AN 
AFTERBURNER WITH AUTOIGNITION AND HOT- 
STREAK IGNITION. P. E. Renas, R. W. Harvey, 
Sr., and E. T. Jansen. April 1953. 25p. diagrs., 
photos., tab. (NACA RM E53B02) 



PRELIMINARY EXPERIMENTAL INVESTIGATION 
OF TRANSPIRATION COOLING FOR AN AFTER- 
BURNER WITH A SINTERED, POROUS STAINLESS- 
STEEL COMBUSTION-CHAMBER WALL. William 
K. Koffel. June 1953. 47p. diagrs., photos., tabs. 
{NACA. RM E53DOB) 



EFFECT OF DIFFUSER DESIGN, DIFFUSER-EXIT 
VELOCITY PROFILE, AND FUEL DISTRIBUTION 
ON ALTITUDE PERFORMANCE OF SEVERAL 
AFTERBURNER CONFIGURATIONS. E. William 
Conrad, Frederick W. Schulze, and Karl H. Usow. 
July 1953. 63p. diagrs., photos., tab. 
(NACA RM E53A30) 



EXPERIMENTAL INVESTIGATION OF SCREECHING 
COMBUSTION IN FULL-SCALE AFTERBURNER. 
Karl H. Usow, Carl L. Meyer, and Frederick W. 
Schulze, December 1953. 62p. diagrs., photos., 
tab. (NACA RM E53I01) 



A SUMMARY OF PRELIMINARY INVESTIGATIONS 
INTO THE CHARACTERISTICS OF COMBUSTION 
SCREECH IN DUCTED BURNERS. Lewis Labora- 
tory Staff. April 1954. 60p. diagrs., photos. 
(NACARM E54B02) 



PERFORMANCE CHARACTERISTICS OF SEVERAL 
SHORT ANNULAR DIFFUSERS FOR TURBOJET 
ENGINE AFTERBURNERS. William E. Mallett and 
James L. Harp, Jr. May 1954. 31p. diagrs., 

photo. (NACA RM E54B09) 



COOLING CHARACTERISTICS OF A 
TRANSPIRATION -COOLED AFTERBURNER WITH A 
POROUS WALL OF BRAZED AND ROLLED WIRE 
CLOTH. William K. Koffel. August 1954. 68p. 
diagrs., photos., tabs. (NACA RM E54E25) 



SOME SCREECHING-COMBUSTION CHARACTER- 
ISTICS OF A TRANSPIRATION -COOLED AFTER- 
BURNER HAVING A POROUS WALL OF WIRE 
CLOTH. William K. Koffel, James L. Harp, Jr., 
and Lively Bryant. November 1954. 12p. diagrs. 
(NACA RM E54H27) 



206 



(3) PROPULSION 



METHODS FOR CALCULATING THRUST AUGMEN- 
TATION AND LIQUID CONSUMPTION FOR VARIOUS 

TURBOJET-AFTERBURNER FUELS. James F. 
Morris. October 1956. 73p. diagrs. 
(NACA RM E56A23) 



ANALYSIS OF TURBOJET-ENGINE CONTROLS FOR 
AFTERBURNER STARTING. W. E. Phillips, Jr. 
October 1956. 6lp. diagrs., tabs. 
(NACA RM E56F29) 



STUDY OF SOME BURNER CROSS-SECTION 
CHANGES THAT INCREASE SPACE-HEATING 
RATES. Donald R. Boldman and Perry L. 
Blackshear, Jr. November 1957. 38p. diagrs. 
photos., tab. (NACA TN 4162) 



EXPERIMENTAL INVESTIGATION OF TURBOJET- 
ENGINE MULTIPLE-LOOP CONTROLS FOR NON- 
AFTERBURNING AND AFTERBURNING MODES OF 
ENGINE OPERATION. Donald B. Kirsch, Leon M. 
Wenzel, and Clint E. Hart. January 1958. 61p. 
diagrs., tab. (NACA TN 4159) 



EFFECT OF PRESSURE AND DUCT GEOMETRY ON 
BLUFF-BODY FLAME STABILIZATION. Andrew E. 
Potter, Jr., and Edgar L. Wong. September 1958. 
31p. diagrs., tab. (NACA TN 4381) 



(3.3.3) 
ROCKET ASSIST 



INFLUENCE OF FUSELAGE-MOUNTED ROCKET- 
BOOSTERS ON FLOW FIELD AT INLET AND ON 
DIFFUSER PERFORMANCE OF STRUT-MOUNTED 
ENGINE AT MACH NUMBERS OF 1.8 AND 2.0. 
George A. Wise and Leonard J. Obery. October 
1952. 16p. diagrs., photos. (NACA RM E 5 2102) 



EFFECT OF FLUID-SYSTEM PARAMETERS ON 
STARTING FLOW IN A LIQUID ROCKET. 
Richard P. Krebs. September 1957. 38p. diagrs., 
tab. (NACA TN 4034) 



(3) PROPULSION 



207 



(3,4) 
Fuels 



EFFECT OF FUEL DENSITY AND HEATING VALUE 
ON RAM-JET AIRPLANE RANGE. Hugh M. 
Henneberry. February 1952. 56p. diagrs., tabs. 
(NACA RM E51L21) 



COMBUSTION OF ALUMINUM BOROHYDKIDE IN A 
SUPERSONIC WIND TUNNEL. Edward A. Fletcher, 
Robert G. Dorsch, and Melvin Gerstein. June 1955. 
72p. diagrs., photos., tabs. (NACA RM E55D07a) 



CALCULATED HEATS OF FORMATION AND COM- 
BUSTION OF BORON COMPOUNDS (BORON, HY- 
DROGEN, CARBON, SILICON). Aubrey P. 
Altshuller. October 1955. 28p. diagrs., tabs. 
(NACA RM E55G26) 



THERMAL DECOMPOSITION OF ETHYLPENTA- 
BORANE IN GAS PHASE. Glen E. McDonald. 
July 1956. 20p. diagrs., tab. (NACA RM E56D26) 



ESTIMATION OF SPECIFIC SURFACE OF FINELY 
DIVIDED MAGNESIUM. Murray L. Pinns. August 
1956. 28p. diagrs., tabs. (NACA RM E56D10a) 



METHODS FOR CALCULATING THRUST AUGMEN- 
TATION AND LIQUID CONSUMPTION FOR VARIOUS 
TURBOJET-AFTERBURNER FUELS. James F. 
Morris. October 1956. 73p. diagrs. 
(NACA RM E56A23) 



SURVEY OF HYDROGEN COMBUSTION PROPER- 
TIES. Isadore L. Drell and Frank E. Belles. 
July 1957. (ii), 86p. diagrs., tabs. 
(NACA RM E57D24) 



(3.4.1) 
PREPARATION 



PREPARATION AND PHYSICAL PROPERTIES OF 
SOME TRIALKYLBORANES. Louis Rosenblum and 
Harrison Allen, Jr. November 1955. I9p. diagrs., 
photos., tab. (NACA RM E55E06) 



DESIGN CONSIDERATIONS OF A CONDENSING 
SYSTEM FOR VAPORIZED MAGNESnjM. Walter 
R. Witzke, George M. Prok, and Thomas A. 
Keller. November 1955. 19p. diagrs., photos., 
tabs. (NACA RM E55I20) 



THERMAL DECOMPOSITION OF ETHYLPENTA- 
BORANE IN GAS PHASE. Glen E. McDonald. 
July 1956. 20p. diagrs., tab. (NACA RM E56D26) 



ESTIMATION OF SPECIFIC SURFACE OF FINELY 
DIVIDED MAGNESIUM. Murray L. Pinns. August 
1956. 28p. diagrs., tabs. (NACA RM E56D10a) 



DROP -SIZE DISTRIBUTION FOR CROSSCURRENT 
BREAKUP OF LIQUID JETS IN AIRSTREAMS. 
Robert D. Ingebo and Hampton H. Foster. 
October 1957. 36p. diagrs., photos, tabs. 
(NACA TN 4087) 



DROP -SIZE DISTRIBUTIONS FOR IMPINGING- JET 
BREAKUP IN AIRSTREAMS SIMULATING THE 
VELOCITY CONDITIONS IN ROCKET COMBUSTORS. 
Robert D. Ingebo. March 1958. 23p. diagrs., 
photos., tab. (NACA TN 4222) 



GRAPHS OF REDUCED VARIABLES FOR COMPUT- 
ING HISTORIES OF VAPORIZING FUEL DROPS, 
AND DROP HISTORIES UNDER PRESSURE. G. L. 
Borman, M. M. El Wakil, O. A. Uyehara, and P. S. 
Myers, University of Wisconsin. September 1958. 
(i), 55p. diagrs., tab. (NACA TN 4338) 



(3.4.2) 

PHYSICAL AND CHEMICAL 

PROPERTIES 



ALUMINUM BOROHYDRIDE AS AN IGNITION 
SOURCE FOR TURBOJET COMBUSTORS. David M. 

Straight, Edward A. Fletcher, and Hampton H. 
Foster. September 1953. 19p. diagrs., photos., 
tabs. (NACA RM E53G15) 



ALUMINUM BOROHYDRIDE - HYDROCARBON MIX- 
TURES AS A SOURCE OF IGNITION FOR A TURBO- 
JET COMBUSTOR. Hampton H. Foster, Edward A. 
Fletcher, and David M. Straight. February 1955. 
24p. diagrs., photo., tabs. (NACA RM E54K12) 



A METHOD FOR THE ANALYSIS OF COMPOUNDS 
CONTAINING BORON, CARBON, AND HYDROGEN. 
Harrison Allen, Jr., and Stanley Tannenbaum. 
March 1955. 9p. diagrs., tabs. 
(NACA RM E54H5) 



CALCULATED HEATS OF FORMATION AND COM- 
BUSTION OF BORON COMPOUNDS (BORON, HY- 
DROGEN, CARBON, SILICON). Aubrey P. 
Altshuller. October 1955. 28p. diagrs., tabs. 
(NACA RM E55G26) 



THE RATE OF DECOMPOSITION OF LIQUID PEN- 
TABORANE FROM 85<> TO 202° C. Glen E. 
McDonald. October 1955. 22p. diagrs., tab. 
(NACA RM E55H01) 



PREPARATION AND PHYSICAL PROPERTIES OF 
SOME TRIALKYLBORANES. Louis Rosenblum and 
Harrison Allen, Jr. November 1955. 19p. diagrs., 
photos., tab. (NACA RM E55E06) 



THEORETICAL PERFORMANCE OF JP-4 FUEL 
WITH A 70-PERCENT-FLUORTNE - 30-PERCENT - 
OXYGEN MDCTURE AS A ROCKET PROPELLANT. 
I - FROZEN COMPOSITION. Sanford Gordon and 
Vearl N. Huff. April 1956. 38p. diagrs., tabs. 
(NACA RM E56A13a) 



A STUDY OF FUEL-NITRIC ACID REACTIVITY. 
Charles E. Feller and Louis Baker, Jr. April 1956. 
48p. diagrs., photo., tabs. (NACA RM E56A19) 



208 



(3) PROPULSION 



TABLES AND CHARTS FOR THERMODYNAMIC 
CALCULATIONS INVOLVING AIR AND FUELS CON- 
TAINING BORON, CARBON, HYDROGEN, AND 
OXYGEN . Eldon W . Hall and Richard J . Weber . 
July 1956. 82p. diagrs., tabs. (NACA RM E56B27) 



THERMAL DECOMPOSITION OF ETHYLPENTA- 
BORANE IN GAS PHASE. Glen E. McDonald. 
July 1956. 20p. diagrs., tab. (NACA RM E56D26) 



ESTIMATION OF SPECIFIC SURFACE OF FINELY 
DIVIDED MAGNESIUM. Murray L. Pinns. August 
1956. 28p. diagrs., tabs. (NACA RM E56D10a) 

THEORETICAL PERFORMANCE OF JP-4 FUEL 
WITH A 70-30 MIXTURE OF FLUORINE AND 
OXYGEN AS A ROCKET PROPELLANT. H - EQUI- 
LIBRIUM COMPOSITION. Sanford Gordon and Vearl 
N. Huff. October 1956. 49p. diagrs., tabs. 
(NACARM E56F04) 



SPONTANEOUS IGNITION OF PENTABORANE 
SPRAYS IN A HOT-AIR STREAM. Erwin A. Lezberg 
and Albert M. Lord. November 1956. 26p. diagrs. 
(NACA RM E55F29a) 



COKING OF JP-4 FUELS IN ELECTRICALLY 
HEATED METAL TUBES. Arthur L. Smith, William 
P. Cook, and Vincent F. Hlavin, November 1956. 
17p. diagrs., tabs. (NACA RM E56H21) 



FUNDAMENTAL FLAME VELOCITY, HEAT OF 
COMBUSTION, AND SPONTANEOUS IGNITION 
TEMPERATURE OF DIMETHYLAMINODIBORANE. 
Robert R. Hibbard and Gordon L. Dugger. 
December 1956. 6p. diagr., tab. 
(NACA RM E52L23) 



THERMAL STABILITY OF PENTABORANE IN THE 
RANGE 329° TO 419° F. Glen E. McDonald. 
December 1956. 4p. diagrs. (NACA RM E54G16) 



THE HEAT OF COMBUSTION OF TETRAETHYLDI- 
BORANE. Stanley Tannenbaum. January 1957. 
5p. tabs. (NACA RM E53E11) 



SPONTANEOUS FLAMMABILITY OF PENTABORANE 

AND PENTABORANE - 3 -ME THY LP E NT AN E 
BLENDS. Edward A. Fletcher. February 1957. 
lip. diagrs., photos. (NACARM E53I17) 



EXPERIMENTAL AND CALCULATED HISTORIES 
OF VAPORIZING FUEL DROPS. R. J. Priem, 
G. L. Borman, M. M. El Wakil, O. A. Uyehara, 
and P. S. Myers, University of Wisconsin. August 
1957. 66p. diagrs. (NACA TN 3988) 



EFFECT OF INITIAL MIXTURE -TEMPERATURE ON 
BURNING VELOCITY OF HYDROGEN-AIR MIX- 
TURES WITH PREHEATING AND SIMULATED 
PREBURNING. Sheldon Heimel. October 1957. 
23p. diagrs., tabs. (NACA TN 4156) 



THEORETICAL ROCKET PERFORMANCE OF 
JP-4 FUEL WITH SEVERAL FLUORINE-OXYGEN 
MDCTURES ASSUMING FROZEN COMPOSITION. 
Sanford Gordon and Kenneth S. Drellishak. 
November 1957. 62p. diagrs. , tabs. 
(NACA RM E57G16a) 



EFFECT OF FUEL VARIABLES ON CARBON FOR- 
MATION IN TURBOJET -ENGINE COMBUSTORS. 
Edmund R. Jonash, Jerrold D. Wear, and William P. 
Cook, 1958. ii, 18p. diagrs., photos., tabs. 
(NACA Rept. 1352. Supersedes RM E52G11, 
RM E52H21, RM E53D15, RM E54H23, RM E55D28, 
RM E55F30a, RM E55J31) 



LOW-TEMPERATURE, VAPOR-PHASE OXIDATION 
OF FUEL-RICH HYDROCARBON MIXTURES. 
William T. House and Milton Orchin, University of 
Cincinnati. January 1958. 30p. diagrs., tabs. 
(NACA TN 4118) 



THEORETICAL ROCKET PERFORMANCE OF JP-4 
FUEL WITH SEVERAL FLUORINE -OXYGEN MIX- 
TURES ASSUMING EQUILIBRIUM COMPOSITION. 
Sanford Gordon. February 1958. 69p. diagrs., 
tabs. (NACA RM E57K22) 



STABILITY OF PROPANE-AIR FLAMES IN VORTEX 
FLOW. A. E. Potter, Jr., E. L. Wong, and A. L. 
Berlad. February 1958. 27p. diagrs., tab. 
(NACA TN 4210) 



THEORETICAL PERFORMANCE OF LIQUID AMMO- 
NIA WITH LIQUID OXYGEN AS A ROCKET PROPEL- 
LANT. Sanford Gordon and Alan R. Glueck. May 
1958. 84p. diagrs., tabs. (NACA RM E58A21) 



THEORETICAL ROCKET PERFORMANCE OF 
LIQUID METHANE WITH SEVERAL FLUORINE- 
OXYGEN MDCTURES ASSUMING FROZEN COMPOSI- 
TION. Sanford Gordon and Michael E. Kastner. 
May 1958. 44p. diagrs., tabs. (NACA RM E58B20) 



GRAPHS OF REDUCED VARIABLES FOR COMPUT- 
ING HISTORIES OF VAPORIZING FUEL DROPS, 
AND DROP HISTORIES UNDER PRESSURE . G. L . 
Borman, M. M. El Wakil, O. A. Uyehara, and P. S. 
Myers, University of Wisconsin. September 1958. 
(i), 55p. diagrs., tab. (NACA TN 4338) 



(3) PROPULSION 



209 



(3.4.3) 

RELATION TO ENGINE 

PERFORMANCE 



INVESTIGATION OF COMBUSTION IN 16-INCH RAM 
JET UNDER SIMULATED CONDITIONS OF HIGH 
ALTITUDE AND HIGH MACH NUMBER. T.J. 
Nussdorfer, D. C. Sederstrom, andE. Perchonok. 
June 27, 1950. 53p. diagrs., photos., tabs. 
(NACARM E50D04) 



COMBUSTION EFFICIENCY PERFORMANCE OF A 
MIL- F- 5624 TYPE FUEL AND MONOMETHYL- 
NAPHTHALENE IN A SINGLE VAPORIZING-TYPE 
COMBUSTOR. Anthony W. Jones and William P. 
Cook. February 1952. 26p. diagrs., photos., tabs. 
(NACARM E51K30) 



EFFECT OF DIFFUSER DESIGN, DIFFUSER-EXIT 
VELOCITY PROFILE, AND FUEL DISTRIBUTION 
ON ALTITUDE PERFORMANCE OF SEVERAL 
AFTERBURNER CONFIGURATIONS. E. William 
Conrad, Frederick W. Schulze, and Karl H. Usow. 
July 1953. 63p. diagrs., photos., tab. 
(NACA RM E53A30) 



INVESTIGATION OF LIQUID FLUORINE - LIQUID 
AMMONIA PROPELLANT COMBINATION IN A 100- 
POUND -THRUST ROCKET ENGINE. Edward A. 
Rothenberg and Howard W. Douglass. July 1953. 
31p. diagrs., photos., tabs. (NACARM E53E08) 



ENGINEERING METHOD OF RAM -JET THRUST 
DETERMINATION BASED ON EXPERIMENTALLY 
OBTAINED COMBUSTOR PARAMETERS. 
H. Rudolph Dettwyler and Maxime A. Faget. August 
1953. 44p. diagrs., tab. (NACA RM L53E21) 



ANALYTIC EVALUATION OF EFFECT OF INLET- 
AIR TEMPERATURE AND COMBUSTION PRESSURE 
ON COMBUSTION PERFORMANCE OF BORON 
SLURRIES AND BLENDS OF PENTABORANE IN 
OCTENE-1. Leonard K. Tower. June 1955. 79p. 
diagrs. (NACA RM E55A31) 



CALCULATED HEATS OF FORMATION AND COM- 
BUSTION OF BORON COMPOUNDS (BORON, HY- 
DROGEN, CARBON, SILICON). Aubrey P. 
Altshuller. October 1955. 28p. diagrs., tabs. 
(NACA RM E55G26) 



ANALYTIC EVALUATION OF EFFECT OF INLET- 
AIR TEMPERATURE AND COMBUSTION PRESSURE 
ON COMBUSTION PERFORMANCE OF BORON 
SLURRIES AND BLENDS OF PENTABORANE IN 
OCTENE-1. SUPPLEMENT I - INFLUENCE OF 
NEW BORIC-OXIDE VAPOR-PRESSURE DATA ON 
CALCULATED PERFORMANCE OF PENTABORANE. 
Leonard K. Tower. May 1956. lip. diagrs. - 
(NACA RM E56D02) 



TABLES AND CHARTS FOR THERMODYNAMIC 
CALCULATIONS INVOLVING AIR AND FUELS CON- 
TAINING BORON, CARBON, HYDROGEN, AND 
OXYGEN. EldonW. Hall and Richard J . Weber. 
July 1956. 82p. diagrs., tabs. (NACA RM E56B27) 



METHODS FOR CALCULATING THRUST AUGMEN- 
TATION AND LIQUID CONSUMPTION FOR VARIOUS 
TURBOJET- AFTERBURNER FUELS. James F. 
Morris. October 1956. 73p. diagrs. 

(NACARM E56A23) 



COKING OF Jr-4 FUELS IN ELECTRICALLY 
HEATED METAL TUBES. Arthur L. Smith, William 
P. Cook, and Vincent F. Hlavin. November 1956. 
17p. diagrs., tabs. (NACA RM E56H21) 



INVESTIGATION OF 70 PERCENT TRIMETHYL 
BORATE - 30 PERCENT METHYL ALCOHOL FUEL 
MIXTURE IN A SINGLE J33 COMBUSTOR AND IN A 
J33 TURBOJET ENGINE. Louis J. Schafer, Jr., 
and Robert 0. Hickel. January 1957. 26p. diagrs., 
photos., tab. (NACA RM E53C24) 



PROPELLANT VAPORIZATION AS A CRITERION 
FOR ROCKET ENGINE DESIGN; CALCULATIONS 
OF CHAMBER LENGTH TO VAPORIZE A SINGLE 
n -HEPTANE DROP. Richard J. Priem. July 1957. 
41p. diagrs., tab. (NACA TN 3985) 



PROPELLANT VAPORIZATION AS A CRITERION 
FOR ROCKET -ENGINE DESIGN; CALCULATIONS 
USING VARIOUS LOG -PROBABILITY DISTRIBU- 
TIONS OF HEPTANE DROPS. Richard J. Priem. 
October 1957. 29p. diagrs., tab. (NACA TN 4098) 



EFFECT OF FUEL VARIABLES ON CARBON FOR- 
MATION IN TURBOJET -ENGINE COMBUSTORS. 
Edmund R. Jonash, Jerrold D. Wear, and William P. 
Cook. 1958. ii, 18p. diagrs., photos., tabs. 
(NACA Rept. 1352. Supersedes RM E52G11, 
RME52H21, RM E53D15, RM E54H23, RM E55D28, 
RM E55F30a, RM E55J31) 



PROPELLANT VAPORIZATION AS A CRITERION 
FOR ROCKET ENGINE DESIGN; RELATION BE- 
TWEEN PERCENTAGE OF PROPELLANT VAPOR- 
IZED AND ENGINE PERFORMANCE: Marcus F. 
Heidmann and Richard J. Priem. March 1958. 
19p, diagrs. (NACA TN 4219) 



PROPELLANT VAPORIZATION AS A CRITERION 
FOR ROCKET -ENGINE DESIGN; CALCULATIONS 
OF CHAMBER LENGTH TO VAPORIZE VARIOUS 
PROPELLANTS. Richard J. Priem. September 
1958. 36p. diagrs., tab. (NACA TN 3883) 



(3.4.3.2) 

TURBINE ENGINES, RAM JETS, 

AND PULSE JETS 



EFFECT OF FUEL VOLATILITY ON ALTITUDE 
STARTING LIMITS OF A TURBOJET ENGINE. 
H. D. Wilsted and J. C. Armstrong. September 11, 
1950. 27p. diagrs., tabs. (NACA RM E50G10) 



TURBOJET COMBUSTOR EFFICIENCY AT HIGH 
ALTITUDES. Walter T. Olson, J. Howard ChUda, 
and Edmund R. Jonash. October 27, 1950. 51p. 
diagrs., photo. (NACA RM E50I07) 



VAPOR- FUEL-DISTRIBUTION EFFECTS ON COM- 
BUSTION PERFORMANCE OF A SINGLE TUBULAR 
COMBUSTOR. Richard J. McCafferty. 
December 13, 1950. 27p. diagrs., photo. 
(NACA RM E50J03) 



LIQUID-FUEL-DISTRIBUTION AND FUEL-STATE 
EFFECTS ON COMBUSTION PERFORMANCE OF A 
SINGLE TUBULAR COMBUSTOR . Richard J . 
McCafferty. May 1, 1951. 38p. diagrs., tab. 
(NACARME51B21) 



COMBUSTION EFFICIENCY PERFORMANCE OF A 
MIL-F-5624 TYPE FUEL AND MONOMETHYL- 
NAPHTHALENE IN A SINGLE VAPORIZING-TYPE 
COMBUSTOR. Anthony W. Jones and William P. 
Cook. February 1952. 26p. diagrs., photos., tabs. 
(NACARME51K30) 



210 



(3) PROPULSION 



EFFECT OF FUEL DENSITY AND HEATING VALUE 
ON RAM -JET AIRPLANE RANGE. Hugh M. 
Henneberry. February 1952. 56p. diagrs., tabs. 
(NACA RM E51L21) 



EFFECT OF WATER VAPOR ON COMBUSTION OF 
MAGNESIUM-HYDROCARBON SLURRY FUELS IN 

SMALL-SCALE AFTERBURNER. Leonard K. 
Tower. October 1952. 39p. diagrs., tabs 
(NACA RM E52H25) 



PRELIMINARY INVESTIGATION OF AN ANNULAR 
TURBOJET COMBUSTOR HAVING A CATALYTIC- 
COATED LINER. Carl T. Norgren and J. Howard 
Childs. January 1954. lip. diagrs. (NACA 
RM E53L07) 



FLIGHT AND PRE FLIGHT TESTS OF A RAM JET 
BURNING MAGNESIUM SLURRY FUEL AND 
UTILIZING A SOLID-PROPELLANT GAS GENERA- 
TOR FOR FUEL EXPULSION. Walter A. Bartlett, 
Jr., and William K. Hagginbothom, Jr. April 1955. 
35p. diagrs., photos. (NACA RM L55A24) 



ANALYTIC EVALUATION OF EFFECT OF INLET- 
AIR TEMPERATURE AND COMBUSTION PRESSURE 
ON COMBUSTION PERFORMANCE OF BORON 
SLURRIES AND BLENDS OF PENTABORANE IN 
OCTENE-1. Leonard K. Tower. June 1955. 79p. 
diagrs. (NACA RM E55A31) 



EFFECTS OF INLET -AIR -FLOW DISTORTION ON 
STEADY-STATE ALTITUDE PERFORMANCE OF AN 
AXIAL-FLOW TURBOJET ENGINE . William 
Conrad, Morgan P. Hanson, and John E. McAulay. 
September 1955. 47p. diagrs., photo. 
(NACARM E55A04) 



CALCULATED HEATS OF FORMATION AND COM- 
BUSTION OF BORON COMPOUNDS (BORON, HY- 
DROGEN, CARBON, SILICON). Aubrey P. 
Altshuller. October 1955. 28p. diagrs., tabs. 
(NACA RM E55G26) 



DESIGN CONSIDERATIONS OF A CONDENSING 
SYSTEM FOR VAPORIZED MAGNESIUM. Walter 
R. Witzke, George M. Prok, and Thomas A. 
Keller. November 1955. 19p. diagrs., photos., 
tabs. (NACA RM E55I20) 



ANALYTIC EVALUATION OF EFFECT OF INLET- 
AIR TEMPERATURE AND COMBUSTION PRESSURE 
ON COMBUSTION PERFORMANCE OF BORON 
SLURRIES AND BLENDS OF PENTABORANE IN 
OCTENE-1. SUPPLEMENT 1 - INFLUENCE OF 
NEW BORIC-OXIDE VAPOR-PRESSURE DATA ON 
CALCULATED PERFORMANCE OF PENTABORANE. 
. Leonard K. Tower. May 1956. ilp. diagrs. 
(NACA RM E56D02) 



PREFLIGHT AND FLIGHT-TEST INVESTIGATION 
OF A 50-PERCENT-MAGNESnjM 50-PERCENT 
JP-4 SLURRY FUEL IN A TWIN-ENGINE RAM-JET 
VEHICLE. Otto F. Trout, Jr., and Thomas L. 
Kennedy. May 1956. 27p. diagrs., photos. 
(NACA RM L56C06) 



TABLES AND CHARTS FOR THERMODYNAMIC 
CALCULATIONS INVOLVING AIR AND FUELS CON- 
TAINTOG BORON, CARBON, HYDROGEN, AND 
OXYGEN. EldonW. Hall and Richard J. Weber. 
July 1956. 82p. diagrs., tabs. (NACARM E56B27) 



SPONTANEOUS IGNITION OF PENTABORANE 
SPRAYS IN A HOT-AIR STREAM. Erwin A. Lezberg 
and Albert M. Lord. November 1956. 26p. diagrs. 
(NACA RM E55F29a) 



COKING OF JP-4 FUELS R>f ELECTRICALLY 
HEATED METAL TUBES. Arthur L. Smith, William 
P. Cook, and Vincent F. Hlavin. November 1956. 
17p. diagrs., tabs. (NACA RM E56H21) 



THERMAL STABILITY OF PENTABORANE IN THE 
RANGE 3290 TO 419° F. Glen E. McDonald 
December 1956. 4p. diagrs. (NACA RM E54G16) 



BASIC CONSIDERATIONS IN THE COMBUSTION OF 
HYDROCARBON FUELS WITH AIR. Propulsion 
Chemistry Division. Edited by Henry C Barnett and 
Robert R. Hibbard. Chap. I: ATOMIZATION AND 
EVAPORATION OF LIQUID FUELS. Charles C. 
Graves and Donald W. Bahr. Chap. H: FLOW AND 
MIXING PROCESSES IN COMBUSTION CHAMBERS. 
Wilfred E. Scull and William R. Mickelsen. 
Chap. HI: IGNITION AND FLAMMABILITY OF 
HYDROCARBON FUELS. Frank E. Belles and 
Clyde C. Swett. Chap. IV: LAMINAR FLAME 
PROPAGATION. Gordon L. Dugger, Dorothy M. 
Simon, and Melvin Gerstein. Chap. V: TURBU- 
LENT FLAMES. Melvin Gerstein and Gordon L. 
Dugger. Chap. VI: FLAME STABILIZATION'. 
Gordon L. Dugger and Melvin Gerstein. Chap. VH: 
DIFFUSION FLAMES. Richard S. Brokaw and 
Melvin Gerstein. Chap. VHI: OSCILLATIONS IN 
COMBUSTORS. Perrv L. Blackshear. Jr.. and 
Warren D. Rayle. Chap. LX: SMOKE AND COKE 
FORMATION IN THE COMBUSTION OF 
HYDROCARBON-AIR MDCTURES. Rose L. Schalla 
and Robert R. Hibbard. 1957. xi, 259p. diagrs., 
photos., tabs. (NACA Rept. 1300) 



INVESTIGATION OF 70 PERCENT TRIMETHYL 
BORATE - 30 PERCENT METHYL ALCOHOL FUEL 
MLXTURE IN A SINGLE J33 COMBUSTOR AND IN A 
J33 TURBOJET ENGINE. Louis J. Schafer, Jr., 
and Robert O. Hickel. January 1957. 26p. diagrs., 
photos., tab. (NACA RM E53C24) 



PERFORMANCE OF AN EXPERIMENTAL ANNULAR 
TURBOJET COMBUSTOR WITH METHANE AND 
PROPANE. Carl T. Norgren. January 1957. 27p. 
diagrs., tabs. (NACA RM E56J22) 



FLIGHT INVESTIGATION OF A RAM JET BURNING 
MAGNESIUM SLURRY FUEL AND HAVING A CONI- 
CAL SHOCK INLET DESIGNED FOR A MACH NUM- 
BER OF 4.1. Walter A. Bartlett, Jr., and 
Charles F. Merlet. January 1957. 23p. diagrs., 
photos. (NACA RM L56I24a) 



A STUDY OF LIQUID BORIC OXIDE PARTICLE 
GROWTH RATES IN A GAS STREAM FROM A SIM- 
ULATED JET ENGINE COMBUSTOR. Paul C. 
Setze. April 1957. 41p. diagrs., photos., tab. 
(NACA RM E55I20a) 



DROP BURNING RATES OF HYDROCARBON AND 
NONHYDROCARBON FUELS- Arthur L. Smith and 
Charles C. Graves. August 1957. 22p. diagrs., 
photos., tabs. (NACA RM E57F11) 



DROP -SIZE DISTRIBUTION FOR CROSSCURRENT 
BREAKUP OF LIQUID JETS IN AIRSTREAMS. 
Robert D. Ingebo and Hampton H. Foster. 
October 1957. 36p. diagrs., photos, tabs. 
(NACA TN 4087) 



EFFECT OF INITIAL MIXTURE -TEMPERATURE ON 
BURNING VELOCITY OF HYDROGEN-AIR MIX- 
TURES WITH PREHEATING AND SIMULATED 
PREBURNTNG. Sheldon Heimel. October 1957. 
23p. diagrs., tabs. (NACA TN 4156) 



(3) PROPULSION 



211 



(3,4.3,3) 

ROCKETS (INCLUDES FUEL 

AND OXIDANT) 



PRELIMINARY INVESTIGATION OF A CHEMICAL 
STARTING TECHNIQUE FOR THE ACID GASOLINE 
ROCKET PROPELLANT SYSTEM. Glen Hennings 
and Gerald Morrell. January 1953. 23p. photo., 
diagrs., tab. (NACA RM E52K21) 



INVESTIGATION OF LIQUID FLUORINE - LIQUID 
AMMONIA PROPELLANT COMBINATION IN A 100- 
POUND-THRUST ROCKET ENGINE. Edward A. 

Rothenberg and Howard W. Douglass. July 1953. 
31p. diagrs., photos., tabs. (NACA RM E53E08) 



CALCULATED HEATS OF FORMATION AND COM- 
BUSTION OF BORON COMPOUNDS (BORON, HY- 
DROGEN, CARBON, SILICON). Aubrey P. 
Altshuller. October 1955. 28p. diagrs., tabs. 
(NACA RM E55G26) 



THEORETICAL PERFORMANCE OF JP-4 FUEL 
WITH A 70-PERCENT-FLUORINE - 30-PERCENT - 
OXYGEN MTXTURE AS A ROCKET PROPELLANT. 
I - FROZEN COMPOSITION. Sanford Gordon and 
VearlN. Huff. April 1956. 38p. diagrs., tabs. 
(NACA RM E56A13a) 



A STUDY OF FUEL-NITRIC ACID REACTrvTIT. 
Charles E. Feller and Louis Baker, Jr. April 1956. 
48p. diagrs., photo., tabs. (NACA RM E56A19) 



EFFECT OF FUELS ON SCREAMING IN 200- 
POUND-THRUST LIQUID-OXYGEN - FUEL ROCKET 
ENGINE. Isaac Pass and Adelbert O. Tischler. 
June 1956. 25p. diagrs., photos., tab. 
(NACA RM E56C10) 



INJECTION PRINCIPLES FOR LIQUID OXYGEN AND 
HEPTANE USING TWO-ELEMENT INJECTORS. 
Marcus F. Heidmann. June 1956. 30p. diagrs., 
photos., tab. (NACA RM E56D04) 



THEORETICAL PERFORMANCE OF JP-4 FUEL 
WITH A 70-30 MIXTURE OF FLUORINE AND 
OXYGEN AS A ROCKET PROPELLANT. H - EQUI- 
HBRRJM COMPOSITION. Sanford Gordon and Vearl 
N. Huff. October 1956. 49p. diagrs., tabs. - 
(NACARME56F04) 



EFFECTS OF VARIATIONS IN COMBUSTION- 
CHAMBER CONFIGURATION ON IGNITION DELAY 
IN A 50-POUND-THRUST ROCKET. Dezso J. 
Ladanyi. October 1956. 53p. diagrs., photos., tabs. 
(NACARM E56F22) 



THERMAL STABILITY OF PENTABORANE IN THE 

RANGE 329« TO 419° F. Glen E. McDonald. 
December 1956. 4p. diagrs. (NACA RM E54G16) 



A STUDY OF INJECTION PROCESSED FOR LIQUID 
OXYGEN AND GASEOUS HYDROGEN IN A 200- 
POUND-THRUST ROCKET ENGINE. Carmon M. 
Auble. January 1957. 32p. diagrs., photos. ^ 
(NACA RM E 56125a) 



PROPELLANT VAPORIZATION AS A CRITERION 
FOR ROCKET-ENGINE DESIGN; EXPERIMENTAL 
EFFECT OF FUEL TEMPERATURE ON LIQUID- 
OXYGEN - HEPTANE PERFORMANCE. M. F. 
Heidmann. July 1957 21p. diagrs., tabs. 
(NACA RM E57E03) 



INJECTION PRINCIPLES FOR LIQUID OXYGEN AND 
HEPTANE USING NINE-ELEMENT INJECTORS IN 
AN 1800-POUND-THRUST ROCKET ENGINE. 
Richard F. Neu. July 1957. 27p. diagrs., photos., 
tab. (NACA RM E57E13) 



NONMETALLIC MATERIAL COMPATIBILITY WITH 
LIQUID FLUORINE. Harold G. Price, Jr., and 
Howard W. Douglass. October 1957. 7p. tab. 
(NACA RM E57G18) 



SUMMARY OF NACA RESEARCH ON IGNITION LAG 
OF SELF-IGNITING FUEL - NITRIC ACID PRO- 
PELLANTS. Gerald Morrell. October 1957. 48p. 
diagrs., photos., tabs. (NACA RM E57G19) • 



THEORETICAL ROCKET PERFORMANCE OF 
JP-4 FUEL WITH SEVERAL FLUORINE-OXYGEN 
MDCTURES ASSUMING FROZEN COMPOSITION. 
Sanford Gordon and Kenneth S. Drellishak. 
November 1957. 62p. diagrs. , tabs. 
(NACA RM E57G16a) 



EFFECT OF FUEL-ORIFICE DIAMETER ON PER- 
FORMANCE OF HEPTANE-OXYGEN ROCKET 
ENGINES. Richard J. Priem and Martin Hersch. 
February 1958. 20p. diagrs. (NACA RM E 57126) 



THEORETICAL ROCKET PERFORMANCE OF JP-4 
FUEL WITH SEVERAL FLUORINE-OXYGEN MIX- 
TURES ASSUMING EQUILIBRIUM COMPOSITION. 
Sanford Gordon. February 1958. 69p. diagrs., 
tabs. (NACA RM E57K22) 



DROP-SIZE DISTRIBUTIONS FOR IMPINGING-JET 
BREAKUP IN AIRSTREAMS SIMULATING THE 
VELOCITY CONDITIONS IN ROCKET COMBUSTORS. 
Robert D. Ingebo. March 1958. 23p. diagrs., 
photos., tab. (NACA TN 4222) 



DILUTION OF LIQUID OXYGEN WHEN NITROGEN 
IS USED FOR PRESSURIZATION. Thomas J. Walsh, 
R. R. Hibbard, and Paul M. Ordin. April 1958. 
17p. diagrs. (NACA RM E58A03a) 



THEORETICAL PERFORMANCE OF LIQUID AMMO- 
NIA WITH LIQUID OXYGEN AS A ROCKET PROPEL- 
LANT. Sanford Gordon and Alan R. Glueck. May 
1958. 84p. diagrs., tabs. (NACA RM E58A21) 



THEORETICAL ROCKET PERFORMANCE OF 
LIQUID METHANE WITH SEVERAL FLUORINE- 
OXYGEN MIXTURES ASSUMING FROZEN COMPOSI- 
TION. Sanford Gordon and Michael E. Kastner. 
May 1958. 44p. diagrs., tabs. (NACA RM E58B20) 



SCREAMING TENDENCY OF THE GASEOUS- 
HYDROGEN - LIQUID-OXYGEN PROPELLANT 
COMBINATION. Louis Baker, Jr., and Fred W. 
Steffen. September 1958. 24p. diagrs., photos., 
tabs. (NACA RM E58E09) 



COMBUSTOR PERFORMANCE WITH VARIOUS 
HYDROGEN-OXYGEN INJECTION METHODS IN A 
200-POUND-THRUST ROCKET ENGINE. M. F. 
Heidmann and Louis Baker, Jr. September 1958. 
45p. diagrs., photos., tab. (NACARM E58E21) 



A MACH 4 ROCKET-POWERED SUPERSONIC TUN- 
NEL USING AMMONIA -OXYGEN AS WORKING 
FLUID. Robert W. Graham, Eleanor Costilow 
Guentert, and Vearl N. Huff. September 1958. 53p. 
diagrs., photos. (NACA TN 4325) 



212 

(3) PROPULSION 



RATE OF REACTION OF GASEOUS FLUORINE 
WITH WATER VAPOR AT 35° C. Vernon A. Slabey 
and Edward A. Fletcher. September 1958. 16p. 
diagrs., tabs. (NACA TN 4374) 



(3) PROPULSION 



213 



(3.5) 
Combustion and Combusfers 



EXPERIMENTAL INVESTIGATION OF TAIL-PIPE- 
BURNER DESIGN VARIABLES. W. A. Fleming, 
E. William Conrad, and A. W. Young. March 5, 
1951. 75 p. diagrs., photos., tab. 
(NACA RM E50K22) 



ALTITUDE PERFORMANCE INVESTIGATION OF 
SINGLE- AND DOUBLE-ANNULAR TURBOJET- 
ENGINE COMBUSTORS WITH VARIOUS SIZE FUEL 
NOZZLES. James L. Harp, Jr., and Kenneth R. 
Vincent. June 1952. 60p. photos., diagrs., tab. 
(NACARM E51L14) 



TURBOJET COMBUSTOR EFFICIENCY WITH 
CERAMIC -COATED LINERS AND WITH MECHANI- 
CAL CONTROL OF FUEL WASH ON WALLS. 
Helmut F. Butze and Edmund R. Jonash. November 
1952. 43p. photos., diagrs., tabs. 
(NACA RM E 5 2125) 



EFFECT OF FUEL INJECTOR LOCATION AND 
MKTURE CONTROL ON PERFORMANCE OF A 
16-INCH RAM- JET CAN -TYPE COMBUSTOR. 
A. J. Cervenka, Eugene Perchonok, and E. E. 
Dangle. July 1953. 33p. diagrs., tab. (NACA 
RM E53F15) 



ENGINEERING METHOD OF RAM -JET THRUST 
DETERMINATION BASED ON EXPERIMENTALLY 
OBTAINED COMBUSTOR PARAMETERS. 
H. Rudolph Dettwyler and Maxime A. Faget. August 
1953. 44p. diagrs., tab. (NACA RM L53E21) 



EFFECT OF INLET-AIR TEMPERATURE ON PER- 
FORMANCE OF A 16-mCH RAM-JET COMBUSTOR. 
A. J. Cervenka, E. E. Dangle, and Robert 
Friedman. October 1953. 24 p. diagrs., tab. 
(NACA RM E53I03) 



EXPERIMENTAL DETERMINATION OF GAS MO- 
TION ACCOMPANYING SCREECHING COMBUSTION 
IN A 6-INCH SIMULATED AFTERBURNER. Perry 
L. Blackshear, Warren D. Rayle, and Leonard K. 
Tower. December 1953 63p. diagrs., photos .. tab. 
(NACA RM E53I28) 



EFFECT OF MECHANICALLY INDUCED SINUSOIDAL 
AIR-FLOW OSCILLATIONS ON OPERATION OF A 
RAM -JET ENGINE. E. E. Dangle, A. J. Cervenka, 
and Eugene Perchonok. June 1954. 24p. diagrs., 
tab. (NACA RM E54D01) 



PERFORMANCE OF A 16-INCH RAM-JET ENGINE 
WITH A CAN-TYPE COMBUSTOR AT MACH NUM- 
BERS OF 1.50 TO 2.16. Donald P. Hearth and 
Eugene Perchonok. August 1954. 30p. diagrs. 
(NACA RM E54G13) 



ANALYTIC EVALUATION OF EFFECT OF INLET- 
AIR TEMPERATURE AND COMBUSTION PRESSURE 
ON COMBUSTION PERFORMANCE OF BORON 
SLURRIES AND BLENDS OF PENTABORANE IN 

OCTENE-1. Leonard K. Tower. June 1955. 79p. 
diagrs. (NACA RM E55A31) 



EXPERIMENTAL EVALUATION OF BORON - 
HYDROCARBON SLURRY IN A 16-INCH RAM-JET 
COMBUSTOR. William R. Kerslake, E. E. Dangle, 
and A. J. Cervenka. June 1955. 37p. diagrs., 
photos., tabs. (NACA RM E55C07) 



ANALYTIC EVALUATION OF EFFECT OF INLET- 
AIR TEMPERATURE AND COMBUSTION PRESSURE 
ON COMBUSTION PERFORMANCE OF BORON 
SLURRIES AND BLENDS OF PENTABORANE IN 
OCTENE-1. SUPPLEMENT I - INFLUENCE OF 
NEW BORIC-OXIDE VAPOR-PRESSURE DATA ON 
CALCULATED PERFORMANCE OF PENTABORANE. 
Leonard K. Tower. May 1956. lip. diagrs. 
(NACA RME56D02) 



METHODS FOR CALCULATING THRUST AUGMEN- 
TATION AND LIQUID CONSUMPTION FOR VARIOUS 
TURBOJET-AFTERBURNER FUELS. James F- 
Morris. October 1956. 73p. diagrs. 
(NACARME56A23) 



THEORETICAL ANALYSIS OF TOTAL-PRESSURE 
LOSS AND AIRFLOW DISTRIBUTION FOR TUBULAR 
TURBOJET COMBUSTORS WITH CONSTANT ANNU- 
LUS AND LINER CROSS -SECTIONAL AREAS. 
Charles C. Graves and Jack S. Grobman. January 
1957. 85p. diagrs., tab. (NACA RM E56I04) 



STABILITY OF PROPANE-AIR FLAMES IN VORTEX 
FLOW. A. E. Potter, Jr., E. L. Wong, and A. ' 
Berlad. February 1958. 27p. diagrs., tab. 
(NACA TN 4210) 



DISCHARGE COEFFICIENTS FOR COMBUSTOR- 
LINER AIR-ENTRY HOLES. H - FLUSH RECTAN- 
GULAR HOLES, STEP LOUVERS, AND SCOOPS. 
Ralph T. Dittrich. April 1958. 56p. diagrs., tab. 
(NACA TN 3924) 



(3.5.1) 

GENERAL COMBUSTION 

RESEARCH 



TURBOJET COMBUSTOR EFFICIENCY WITH 
CERAMIC-COATED LINERS AND WITH MECHANI- 
CAL CONTROL OF FUEL WASH ON WALLS. 
Helmut F. Butze and Edmund R. Jonash. November 
1952. 43p. photos., diagrs., tabs. 
(NACA RM E52125) 



PRELIMINARY EXPERIMENTS WITH PILOT BURN- 
ERS FOR RAM -JET COMBUSTORS. John M. 
Farley, Robert E. Smith, and John H. Povolny. 
January 1953. 45p. diagrs., photos., tabs. 
(NACARME52J23) 



PRELIMINARY D4VESTIGATION OF AN ANNULAR 
TURBOJET COMBUSTOR HAVING A CATALYTIC- 
COATED LINER. Carl T. Norgren and J. Howard 
Childs. January 1954. lip. diagrs. (NACA 
RM E53L07) 



HIGH-ALTITUDE PERFORMANCE OF 9.5-INCH- 
DIAMETER TUBULAR EXPERIMENTAL COMBUS- 
TOR WITH FUEL STAGING. Wilfred E. Scull. 
March 1954. 55p. diagrs., photos., tabs. 
(NACA RM E54A06) 



A SUMMARY OF PRELIMINARY INVESTIGATIONS 
INTO THE CHARACTERISTICS OF COMBUSTION 
SCREECH IN DUCTED BURNERS. Lewis Labora- 
tory Staff. April 1954. 60p. diagrs., photos. 
(NACARME54B02) 



214 



(3) PROPULSION 



PERFORMANCE OF A PAIR OF TUBULAR COMBUS- 
TpRS WITH AN EXTERNAL PILOT CHAMBER. 
Robert Friedman and Eugene V. Zettle. September 
1954. 26p. diagrs., tab. (NACA RM E54E11) 



PHOTOGRAPHIC INVESTIGATION OF AIR-FLOW 
PATTERNS IN TRANSPARENT ONE-SIXTH SECTOR 
OF ANNULAR TURBOJET-ENGINE COMBUSTOR 
WITH AXIAL-SLOT -TYPE AIR ADMISSION. 
Charles C. Graves and J. Dean Gernon. December 
1954. 24p. diagrs., photos. (NACA RM E 54128a) 



FLIGHT AND PRE FLIGHT TESTS OF A RAM JET 
BURNING MAGNESIUM SLURRY FUEL AND 
UTILIZING A SOLID-PROPELLANT GAS GENERA- 
TOR FOR FUEL EXPULSION. Walter A. Bartlett, 
Jr., and William K. Hagginbothom, Jr. April 1955. 
35p. diagrs., photos. (NACA RM L55A24) 



COMBUSTION OF ALUMINUM BOROHYDRIDE IN A 

SUPERSONIC. WIND TUNNEL. Edward A. Fletcher, 
Robert G. Dorsch, and Melvin Gerstein. June 1955. 
72p. diagrs., photos., tabs. (NACA RM E55D07a) 



EFFECTIVENESS OF A TURBOJET TUBULAR 
COMBUSTOR IN SCREENING THE TURBINE FROM 
FOREIGN OBJECTS- Patrick T. Chiarito. July 
1955. 20p. diagrs., photos. (NACA RM E55E16) 



A PRELIMINARY INVESTIGATION OF STATIC- 
PRESSURE CHANGES ASSOCIATED WITH COMBUS- 
TION OF ALUMINUM BOROHYDRIDE IN A SUPER- 
SONIC WIND TUNNEL. Robert G. Dorsch, John S. 
Serafini, and Edward A. Fletcher. August 1955. 
12p. diagrs., ph tos. (NACA RM E55F07) 



ANALYTICAL COMPARISON OF CONVECTION- 
COOLED TURBINE BLADE COOLING-AIR RE- 
QUIREMENTS FOR SEVERAL RADIAL GAS- 
TEMPERATURE PROFILES. James E. Hubbartt 
and Henry O. Slone. September 1955. 46p. diagrs. 
(NACA RM E55G14) 



PREFLIGHT AND FLIGHT-TEST INVESTIGATION 
OF A 50-PERCENT-MAGNESIUM 50-PERCENT 
JP-4 SLURRY FUEL IN A TWIN -ENGINE RAM- JET 
VEHICLE. Otto F. Trout, Jr., and Thomas L. 
Kennedy. May 1956. 27p. diagrs., photos. 
(NACA RM L56C06) 



RELATION OF TURBOJET AND RAMJET COMBUS- 
TION EFFICIENCY TO SECOND-ORDER REACTION 
KINETICS AND FUNDAMENTAL FLAME SPEED. 
J. Howard Childs, Thaine W. Reynolds, and Charles 
C. Graves. 1957. ii, 13p. diagrs 
(NACARept. 1334) 



THE HEAT OF COMBUSTION OF TETRAETHYLDI- 
BORANE. Stanley Tannenbaum. January 1957. 
5p. tabs. (NACARM E53E11) 



PERFORMANCE OF AN EXPERIMENTAL ANNULAR 
TURBOJET COMBUSTOR WITH METHANE AND 
PROPANE. Carl T. Norgren. January 1957. 27p. 
diagrs., tabs. (NACA RM E56J22) 



FLIGHT INVESTIGATION OF A RAM JET BURNING 
MAGNESIUM SLURRY FUEL AND HAVING A CONI- 
CAL SHOCK INLET DESIGNED FOR A MACH NUM- 
BER OF 4.1. Walter A. Bartlett, Jr., and 
Charles F. Merlet. January 1957. 23p. diagrs., 
photos. (NACA RM L56I24a) 



EXPLORATORY INVESTIGATION OF AERODYNAM- 
IC EFFECTS OF EXTERNAL COMBUSTION OF 
ALUMINUM BOROHYDRIDE IN AIRSTREAM ADJA- 
CENT TO FLAT PLATE IN MACH 2.46 TUNNEL. 
Robert G. Dorsch, JohnS. Serafini, and Edward A. 
Fletcher. July 1957. 91p. diagrs., photos., tabs. 
(NACA RM E57E16) 



EXPERIMENTAL AND CALCULATED HISTORIES 
OF VAPORIZING FUEL DROPS. R. J. Priem, 
G. L. Borman, M. M. El Wakil, O. A. Uyehara, 
and P. S. Myers, University of Wisconsin. August 
1957. 66p. diagrs. (NACA TN 3988) 



EXPLORATORY INVESTIGATION Or STATIC- AND 

BASE -PRESSURE INCREASES RESULTING FROM 
COMBUSTION OF ALUMINUM BOROHYDRIDE 
ADJACENT TO BODY OF REVOLUTION IN SUPER- 
SONIC WIND TUNNEL. John S. Serafini, Robert G. 
Dorsch, and Edward A. Fletcher. October 1957. 
49p. diagrs., photos., tabs. (NACA RM E57E15) 



EFFECT 01 PRESSURE AND DUCT GEOMETRY ON 
BLUFF-BODY FLAME STABILIZATION. Andrew E. 
Potter, Jr., and Edgar L. Wong. September 1958. 
31p. diagrs., tab. (NACA TN 4381) 



(3.5.1.1) 
LAMINAR-FLOW COMBUSTION 



BASIC CONSIDERATIONS IN THE COMBUSTION OF 
HYDROCARBON FUELS WITH AIR. Propulsion 
Chemistry Division. Edited by Henry C. Barnett and 
Robert R. Hibbard. Chap. I: ATOMIZATION AND 
EVAPORATION OF LIQUID FUELS. Charles C. 
Graves and Donald W. Bahr. Chap. II: FLOW AND 
MDONG PROCESSES IN COMBUSTION CHAMBERS. 
Wilfred E. Scull and William R. Mickelsen. 
Chap. HI: IGNITION AND FLAMMABILITY OF 
HYDROCARBON FUELS. Frank E. Belles and 
Clyde C. Swett. Chap. IV: LAMINAR FLAME 
PROPAGATION. Gordon L. Dugger, Dorothy M. 
Simon, and Melvin Gerstein. Chap. V: TURBU- 
LENT FLAMES. Melvin Gerstein and Gordon. L. 
Dugger. Chap. VI: FLAME STABILIZATION . 
Gordon L. Dugger and Melvin Gerstein. Chap. VII: 
DIFFUSION FLAMES. Richard S. Brokaw and 
Melvin Gerstein. Chap. VIH: OSCILLATIONS IN 
COMBUSTORS. Perry L. Blackshea r, Jr ., and 
Warren D. Rayle. Chap. DC: SMOKE AND COKE 
FORMATION IN THE COMBUSTION OF 
HYDROCARBON -AIR MIXTURES. Rose L. Schalla 
and Robert R. Hibbard- 1957. xi, 259p. diagrs., 
photos., tabs. (NACA Rept. 1300) 



SURVEY OF HYDROGEN COMBUSTION PROPER- 
TIES. Isadore L. Drell and Frank E. Belles. 
July 1957. (ii), 86p. diagrs., tabs. 
(NACA RM E57D24) 



STABILITY LIMITS AND BURNING VELOCITIES 
FOR SOME LAMINAR AND TURBULENT PROPANE 
AND HYDROGEN FLAMES AT REDUCED PRES- 
SURE. Burton Fine. August 1957. 49p. diagrs., 
tabs. (NACA TN 4031) 



EFFECT OF INITIAL MIXTURE -TEMPERATURE ON 
BURNING VELOCITY OF HYDROGEN-AIR MIX- 
TURES WITH PREHEATING AND SIMULATED 
PREBURNING. Sheldon Heimel. October 1957. 
23p. diagrs., tabs. (NACA TN 4156) 



STUDIES OF OH, CO. CH, AND C 2 RADIATION. 
FROM LAMINAR AND TURBULENT PROPANE-AIR 
AND ETHYLENE -AIR FLAMES. Thomas P. Clark. 
June 1958. 23p. diagrs., photos. (NACA TN 4266) 



(3) PROPULSION 



215 



(3.5.1.2) 
TURBULENT-FLOW COMBUSTION 



BASIC CONSIDERATIONS IN THE COMBUSTION OF 
HYDROCARBON FUELS WITH AIR. Propulsion 
Chemistry Division. Edited by Henry C. Barnett and 
Robert R. Hibbard. Chap. I: ATOMIZATION AND 
EVAPORATION OF LIQUID FUELS. Charles C. 
Graves and Donald W. Bahr. Chap. H: FLOW AND 
MIXING PROCESSES IN COMBUSTION CHAMBERS. 
Wilfred E. Scull and William R. Mickelsen. 
Chap. Ill: IGNITION AND FLAMMABILITY OF 
HYDROCARBON FUELS. Frank E. Belles and 
Clyde C. Swett. Chap. IV: LAMINAR FLAME 
PROPAGATION. Gordon L. Dugger, porothy M. 
Simon, and Melvin Gerstein. Chap. V: TURBU- 
LENT FLAMES. Melvin Gerstein and Gordon L. 
Dugger. Chap. VI: FLAME STABILIZATION. 
Gordon L. Dugger and Melvin Gerstein. Chap. VII: 
DIFFUSION FLAMES. Richard S. Brokaw and 
Melvin Gerstein. Chap. VIH; OSCILLATIONS IN 
COMBUSTORS. Perry L. Blackshear^ Jr . , and^ 
Warren D. Hayle. Chap. IX: " SMOA.E AND COKE 
FORMATION IN THE COMBUSTION OF 
HYDROCARBON -AIR MDCTURES. Rose L. Schalla 
and Robert R. Hibbard. 1957. xi, 259p. diagrs., 
photos., tabs. (NACA Rept. 1300) 



SURVEY OF HYDROGEN COMBUSTION PROPER- 
TIES. Isadore L. Drell and Frank E. Belles. 
July 1957. (ii), 86p, diagrs., tabs. 
(NACA RM E57D24) 



STABILITY LIMITS AND BURNING VELOCITIES 
FOR SOME LAMINAR AND TURBULENT PROPANE 
AND HYDROGEN FLAMES AT REDUCED PRES- 
SURE. Burton Fine. August 1957. 49p. diagrs., 
tabs. (NACA TN 4031) 



STUDY OF SOME BURNER CROSS-SECTION 
CHANGES THAT INCREASE SPACE-HEATING 
RATES . Donald R . Boldman and Perry L . 
Blackshear, Jr. November 1957. 38p. diagrs., 
photos., tab. (NACA TN 4162) 



STUDIES OF OH, CO, CH, AND C2 RADIATION 
FROM LAMINAR AND TURBULENT PROPANE-AIR 
AND ETHYLENE-AIR FLAMES. Thomas P. Clark. 
June 1958. 23p. diagrs., photos. (NACA TN 4266) 



AN ANALYTICAL STUDY OF TURBULENT AND 
MOLECULAR MIXING IN ROCKET COMBUSTION. 
David A. Bittker. September 1958. 22p. diagrs. 
(NACA TN 4321) 



(3.5.1.3) 

DETONATION 



SURVEY OF HYDROGEN COMBUSTION PROPER- 
TIES. Isadore L. Drell and Frank E. Belles. 
July 1957. (ii), 86p. diagrs., tabs. 
(NACA RM E57D24) 



(3. 5.1.4) 

EFFECTS OF FUEL ATOMIZATION 



TURBOJET COMBUSTOR EFFICIENCY AT HIGH 

ALTITUDES. Walter T. Olson, J. Howard Childs, 
and Edmund R. Jonash. October 27, 1950. 5Ip. 
diagrs., photo. (NACA RM E50I07) 



VAPOR-FUEL-DISTRIBuTION EFFECTS ON COM- 
BUSTION PERFORMANCE OF A SINGLE TUBULAR 

COMBUSTOR. Richard J. McCafferty. 
December 13, 1950. 27p. diagrs., photo. 
(NACARM E50J03) 



LIQUID-FUEL-DISTRIBUTION AND FUEL-STATE 
EFFECTS ON COMBUSTION PERFORMANCE OF A 
SINGLE TUBULAR COMBUSTOR . Richard J . 
McCafferty. May 1, 1951. 38p. diagrs., tab. 

(NACARM E51B21) 



ALTITUDE PERFORMANCE INVESTIGATION OF 

SINGLE- AND DOUBLE-ANNULAR TURBOJET- 
ENGINE COMBUSTORS WITH VARIOUS SIZE FUEL 
NOZZLES. James L. Harp, Jr., and Kenneth R. 
Vincent. June 1952. 60p. photos., diagrs., tab. 
(NACA RM E51L14) 



TURBOJET COMBUSTOR EFFICIENCY WITH 
CERAMIC -COATED LINERS AND WITH MECHANI- 
CAL CONTROL OF FUEL WASH ON WALLS. 
Helmut F. Butze and Edmund R. Jonash. November 
1952. 43p. photos., diagrs., tabs. 
(NACA RM E52I25) 



INJECTION PRINCIPLES FOR LIQUID OXYGEN AND 
HEPTANE USING TWO-ELEMENT INJECTORS. 
Marcus F. Heidmann. June 1956. 30p. diagrs., 
photos., tab. (NACA RM E56D04) 



BASIC CONSIDERATIONS IN THE COMBUSTION OF 
HYDROCARBON FUELS WITH AIR. Propulsion 
Chemistry Division. Edited by Henry C. Barnett and 
Robert R. Hibbard. Chap. I: ATOMIZATION AND 
EVAPORATION OF LIQUID FUELS. Charles C. 
Graves and Donald W. Bahr. Chap. II: FLOW AND 
MIXING PROCESSES IN COMBUSTION CHAMBERS. 
Wilfred E. Scull and William R. Mickelsen. 
Chap. HI: IGNITION AND FLAMMABILITY OF 
HYDROCARBON FUELS, Frank E. Belles and 
Clyde C. Swett. Chap. IV: LAMINAR FLAME 
PROPAGATION. Gordon L. Dugger, Dorothy M. 
Simon, and Melvin Gerstein. Chap. V: TURBU- 
LENT FLAMES. Melvin Gerstein and Gordon L. 
Dugger. Chap. VI: FLAME STABILIZATION. 
Gordon L. Dugger and Melvin Gerstein. Chap. VII: 
DIFFUSION FLAMES. Richard S. Brokaw and 
Melvin Gerstein. Chap. VIH: OSCILLATIONS IN 
COMBUSTORS. Perry L. Blackshear, Jr., and 
Warren D. Rayle. Chap. DC: SMOKE AND COKE 
FORMATION IN THE COMBUSTION OF 
HYDROCARBON-AIR MIXTURES. Rose L. Schalla 
and Robert R. Hibbard. 1957. xi, 259p. diagrs., 
photos., tabs. (NACA Rept. 1300) 



A STUDY OF INJECTION PROCESSES FOR LIQUID 
OXYGEN AND GASEOUS HYDROGEN IN A 200- 
POUND-THRUST ROCKET ENGINE. Carmon M. 
Auble. January 1957. 32p. diagrs., photos. 
(NACA RM E56I25a) 



PERFORMANCE OF AN EXPERIMENTAL ANNULAR 
TURBOJET COMBUSTOR WITH METHANE AND 
PROPANE. Carl T. Norgren. January 1957. 27p. 
diagrs., tabs. (NACA RM E56J22) 



PROPELLANT VAPORIZATION AS A CRITERION 
FOR ROCKET-ENGINE DESIGN; EXPERIMENTAL 
EFFECT OF FUEL TEMPERATURE ON LIQUID- 
OXYGEN - HEPTANE PERFORMANCE. M. F. 
Heidmann. July 1957. 21p. diagrs., tabs. 
(NACA RM E57E03) 



INJECTION PRINCIPLES FOR LIQUID OXYGEN AND 
HEPTANE USING NINE-ELEMENT INJECTORS IN 
AN 1800-POUND-THRUST ROCKET ENGINE. 
Rirhard F. Neu. July 1957. 27p. diagrs., photos., 
tab. (NACA RM E57E13) 



216 



(3) PROPULSION 



EFFECT OF FUEL-ORIFICE DIAMETER ON PER- 
FORMANCE OF HEPTANE -OXYGEN ROCKET 
ENGINES. Richard J. Priera and Martin Hersch. 
February 1958. 20p. diagrs. (NACA RM E57I26) 



PROPELLANT VAPORIZATION AS A CRITERION 
FOR ROCKET ENGINE DESIGN; RELATION BE- 
TWEEN PERCENTAGE OF PROPELLANT VAPOR- 
IZED AND ENGINE PERFORMANCE. Marcus F. 
Heldmann and Richard J. Priem. March 1958. 
19p. diagrs. (NACA TN 4219) 



EFFECT OF FUEL DROP SIZE AND INJECTOR 
CONFIGURATION ON SCREAMING IN A 200-POUND- 
THRUST ROCKET ENGINE USING LIQUID OXYGEN 
AND HEPTANE. Charles E. Feiler. June 1958. 
27p. diagrs., photos., tab. (NACA RM E58A20a) 

COMBUSTOR PERFORMANCE WITH VARIOUS 
HYDROGEN-OXYGEN INJECTION METHODS IN A 
200 -POUND -THRUST ROCKET ENGINE. M. F., 
Heidmann and Louis Baker, Jr. September 1958. 
45p. diagrs., photos., tab. (NACA RM E58E21) 



GRAPHS OF REDUCED VARIABLES FOR COMPUT- 
ING HISTORIES OF VAPORIZING FUEL DROPS, 
AND DROP HISTORIES UNDER PRESSURE. G. L. 
Borman, M. M. El Wakil, O. A. Uyehara, and P. S. 
Myers, University of Wisconsin. September 1958. 
(i), 55p. diagrs., tab. (NACA TN 4338) 



(3.5.1.5) 
REACTION MECHANISMS 



A SUMMARY OF PRELIMINARY INVESTIGATIONS 
INTO THE CHARACTERISTICS OF COMBUSTION 
SCREECH IN DUCTED BURNERS. Lewis Labora- 
tory Staff. April 1954. 60p. diagrs., photos. 
(NACARM E54B02) 



A STUDY OF FUEL-NITRIC ACID REACTIVITY. 
Charles E. Feiler and Louis Baker, Jr. April 1956. 
48p. diagrs., photo., tabs. (NACA RM E56A19) 



EFFECT OF FUELS ON SCREAMING IN 200- 
POUND-THRUST LIQUID-OXYGEN - FUEL ROCKET 
ENGINE. Isaac Pass and Adelbert O. Tischler. 
June 1956. 25p. diagrs., photos., tab. 
(NACA RM E56C10) 



SPONTANEOUS IGNITION OF PENTABORANE 
SPRAYS IN A HOT-AIR STREAM. Erwin A. Lezberg 
and Albert M. Lord. November 1956. 26p. diagrs. 
(NACA RM E55F29a) 



BASIC CONSIDERATIONS IN THE COMBUSTION OF 
HYDROCARBON FUELS WITH AIR. Propulsion 
Chemistry Division. Edited by Henry C. Barnett and 
Robert R. Hibbard. Chap. I: ATOMIZATION AND 
EVAPORATION OF LIQUID FUELS. Charles C. 
Graves and Donald W. Bahr. Chap. H: FLOW AND 
MIXING PROCESSES IN COMBUSTION CHAMBERS. 
Wilfred E. Scull and William R. Mickelsen. 
Chap. DJ: IGNITION AND FLAMMABILITY OF 
HYDROCARBON FUELS. Frank E. Belles and 
Clyde C. Swett. Chap. IV: LAMINAR FLAME 
PROPAGATION. Gordon L. Dugger, Dorothy M. 
Simon, and Melvin Gerstein. Chap. V: TURBU- 
LENT FLAMES. Melvin Gerstein and Gordon L. 
Dugger. Chap. VI: FLAME STABILIZATION. 
Gordon L. Dugger and Melvin Gerstein. Chap. VII: 
DIFFUSION FLAMES. Richard S. Brokaw and 
Melvin Gerstein. Chap. VTH: OSCILLATIONS IN 
COMBUSTORS. Perry L. Blackshear, Jr., and 
Warren D^ Rayle. Chap. IX: SMOKE AND COKE 
FORMATION IN THE COMBUSTION OF 
HYDROCARBON-AIR MTXTURES. Rose L. Schalla 
and Robert R. Hibbard. 1957. xi, 259p. diagrs., 
photos., tabs. (NACA Rept. 1300) 



SURVEY OF HYDROGEN COMBUSTION PROPER- 
TIES. Isadore L. Drell and Frank E. Belles. 
July 1957, (ii), 86p. diagrs., tabs. 
(NACA RM E57D24) 



DROP BURNING RATES OF HYDROCARBON AND 
NONHYDROCARBON FUELS. Arthur L. Smith and 
Charles C. Graves. August 1957. 22p. diagrs., 
photos., tabs. (NACA RM E57F11) 



EFFECT OF INITIAL MDCTURE -TEMPERATURE ON 
BURNING VELOCITY OF HYDROGEN-AIR MTX- 
TURES WITH PREHEATING AND SIMULATED 
PREBURNTNG. Sheldon Heimel. October 1957. 
23p. diagrs., tabs. (NACA TN 4156) 



LOW-TEMPERATURE, VAPOR-PHASE OXIDATION 
OF FUEL-RICH HYDROCARBON MIXTURES. 
William T. House and Milton Orchin, University of 
Cincinnati. January 1958. 30p. diagrs., tabs. 
(NACA TN 4118) 



STUDIES OF OH, CO, CH, AND C 2 RADIATION 
FROM LAMINAR AND TURBULENT PROPANE-Am 
AND ETHYLENE-AIR FLAMES. Thomas P. Clark. 
June 1958. 23p. diagrs., photos. (NACA TN 4266) 



(3. 5.1.6) 

IGNITION OF GASES 



EFFECT OF FUEL VOLATILITY ON ALTITUDE 
STARTING LIMITS OF A TURBOJET ENdNE. 
H. D. Wilsted and J. C. Armstrong. September 11, 
1950. 27p. diagrs., tabs. (NACA RM E50G10) 



INVESTIGATION OF ALTITUDE IGNITION, ACCEL- 
ERATION AND STEADY-STATE OPERATION WITH 
SINGLE COMBUSTOR OF J47 TURBOJET ENGINE. 
William P. Cook and Helmut F. Butze. March 5, 
1951. 35p. diagrs., photo., tab. 
(NACARM E51A25) 



ALUMINUM BOROHYDRIDE AS AN IGNITION 
SOURCE FOR TURBOJET COMBUSTORS. David M. 
Straight, Edward A. Fletcher, and Hampton H. 
Foster. September 1953. 19p. diagrs., photos., 
tabs. (NACA RM E53G15) 



ALUMINUM BOROHYDRIDE - HYDROCARBON MDC- 
TURES AS A SOURCE OF IGNITION FOR A TURBO- 
JET COMBUSTOR. Hampton H. Foster, Edward A. 
Fletcher, and David M. Straight. February 1955. 
24p. diagrs., photo., tabs. (NACA RM E54K12) 



SPARK IGNITION OF FLOWING GASES. Clyde C. 
Swett, Jr. 1956. ii, 18p. diagrs., tabs. 
(NACA Rept. 1287) 



EFFECTS OF VARIATIONS IN COMBUSTION - 
CHAMBER CONFIGURATION ON IGNITION DELAY 
IN A 50-POUND-THRUST ROCKET. Dezso J. 
Ladanyi. October 1956. 53p. diagrs., photos., tabs. 
(NACA RM E56F22) 



SPONTANEOUS IGNITION OF PENTABORANE 
SPRAYS IN A HOT- Affi STREAM. Erwin A. Lezberg 
and Albert M. Lord. November 1956. 26p. diagrs. 
(NACA RM E55F29a) 



(3) PROPULSION 



217 



BASIC CONSIDERATIONS IN THE COMBUSTION OF 
HYDROCARBON FUELS WITH AIR. Propulsion 
Chemistry Division. Edited by Henry C. Barnett and 
Robert R. Hibbard. Chap. I: ATOMIZATION AND 
EVAPORATION OF LIQUID FUELS. Charles C 
Graves and Donald W. Bahr. Chap. II: FLOW AND 
MDONG PROCESSES IN COMBUSTION CHAMBERS. 
Wilfred E. Scull and William R. Mickelsen. 
Chap, m: IGNITION AND FLAMMABILITY OF 
HYDROCARBON FUELS. Frank E. Belles and 
Clyde C. Swett. Chap. IV: LAMINAR FLAME 
PROPAGATION. Gordon L. Dugger, Dorothy M. 
Simon, and Melvin Gersteln. Chap. V: TURBU- 
LENT FLAMES. Melvin Gerstein and Gordon L. 
Dugger. Chap. VI: FLAME STABILIZATION. 
Gordon L. Dugger and Meivin Gerstein. Chap. VH: 
DIFFUSION FLAMES. Richard S. Brokaw and 
Melvin Gerstein. Chap. Vm: OSCILLATIONS IN 
COMBUSTORS. Perry L. Blackshear, Jr., anfl 
Warren D. RayAe. Chap. DC: SMOKE AND COKE 
FORMATION IN THE COMBUSTION OF 
HYDROCARBON -AIR MIXTURES. Rose L. Schalla 
and Robert R. Hibbard. 1957. xi, 259p. diagrs., 
photos., tabs. (NACA Rept. 1300) 



SPONTANEOUS FLAMMABILITY OF PENTABORANE 
AND PENTABORANE - 3-METHYLPENTANE 
BLENDS. Edward A. Fletcher. February 1957. 
lip. diagrs., photos. (NACA RM E 5 31 17) 



SURVEY OF HYDROGEN COMBUSTION PROPER- 
TIES. Isadore L. Drell and Frank E. Belles. 
July 1957. (ii), 86p. diagrs., tabs. 
(NACA RM E57D24) 



PRELIMINARY INVESTIGATION OF PROPANE 
COMBUSTION IN A 3 -INCH -DIAMETER DUCT AT 
IN LET -AIR TEMPERATURES OF 1400° TO 1600° F. 
Erwin A. Lezberg. July 1957. 19p. diagrs., 
photos., tab. (NACA TN 4028) 



LOW-TEMPERATURE, VAPOR-PHASE OXIDATION 
OF FUEL-RICH HYDROCARBON MIXTURES. 
William T. House and Milton Orchin, University of 
Cincinnati. January 1958. 30p. diagrs., tabs. 
(NACA TN 4118) 



(3.5.2) 
EFFECT OF ENGINE OPERATING 
CONDITIONS AND COMBUSTION 
CHAMBER GEOMETRY 



INVESTIGATION OF EFFECTS OF SEVERAL FUEL- 
INJECTION LOCATIONS ON OPERATIONAL PER- 
FORMANCE OF A 20-INCH RAM JET. W. H. 
Sterbentz, E. Perehonok, and F. A. Wilcox. 
June 8, 1948. 39p. diagrs., photos. 
{NACA RM EVL02) 



ALTITUDE-WIND-TUNNEL INVESTIGATION OF 
TAIL-PIPE BURNER WITH CONVERGING CONICAL 
BURNER SECTION ON J35-A-5 TURBOJET ENGINE. 
H. Carl Thorman and Carl E. Campbell. 
February 10, 1950. 60p. diagrs., photos., tab. 
(NACA RM E9I16) 



ALTITUDE PERFORMANCE AND OPERATIONAL 
CHARACTERISTICS OF 29-INCH-DIAMETER TAIL- 
PIPE BURNER WITH SEVERAL FUEL SYSTEMS 
AND FUEL-COOLED STAGE-TYPE FLAME 
HOLDERS ON J35-A-5 TURBOJET ENGINE. 
Richard L. Golladay and Harry E. Bloomer. 
April 28, 1950. 57p. diagrs., photos., tab. 
(NACA RM E50A19) 



INVESTIGATION OF ALTITUDE IGNITION, ACCEL- 
ERATION AND STEADY-STATE OPERATION WITH 
SINGLE COMBUSTOR OF J47 TURBOJET ENGINE. 
William P. Cook and Helmut F. BuUe. March 5, 
1951. 35p. diagrs., photo., tab. 
(NACA RM E51A25) 



COMBUSTION EFFICIENCY PERFORMANCE OF A 
MIL-F-5624 TYPE FUEL AND MONOMETHYL- 
NAPHTHALENE IN A SINGLE VAPORIZING-TYPE 
COMBUSTOR. Anthony W. Jones and William P. 
Cook. February 1952. 26p. diagrs., photos., tabs. 
(NACARME51K30) 



TURBOJET COMBUSTOR EFFICIENCY WITH 
CERAMIC -COATED LINERS AND WITH MECHANI- 
CAL CONTROL OF FUEL WASH ON WALLS. 
Helmut F. Butze and Edmund R. Jonash. November 
1952. 43p. photos., diagrs., tabs. 
(NACA RM E 52125) 



ALTITUDE PERFORMANCE INVESTIGATION OF 
TWO SINGLE-ANNULAR TYPE COMBUSTORS AND 
THE PROTOTYPE J40-WE-8 TURBOJET ENGINE 
COMBUSTOR WITH VARIOUS COMBUSTOR INLET- 
AIR PRESSURE PROFILES. Adam E. Sobolewski, 
Robert R. Miller, and John E. McAulay. May 1953. 
46p. diagrs.. photos., tab. (NACA RM E52J07) 



EFFECT OF DIFFUSER DESIGN, DIFFUSER-EXIT . 
VELOCITY PROFILE, AND FUEL DISTRIBUTION 
ON ALTITUDE PERFORMANCE OF SEVERAL 
AFTERBURNER CONFIGURATIONS. E. William 
Conrad, Frederick W. Schulze, and Karl H. Usow. 
July 1953. 63p. diagrs., photos., tab. 
(NACA RM E53A30) 



ENGINEERING METHOD OF RAM -JET THRUST 
DETERMINATION BASED ON EXPERIMENTALLY 
OBTAINED COMBUSTOR PARAMETERS. 
H. Rudolph Dettwyler and Maxime A. Faget. August 
1953. 44d. diagrs., tab. (NACA RM L53E21) 



EFFECT OF INLET -AIR TEMPERATURE ON PER- 
FORMANCE OF A 16-INCH RAM-JET COMBUSTOR. 
A. J. Cervenka, E. E. Dangle, and Robert 
Friedman. October 1953. 24 p. diagrs., tab. 
(NACA RM E53I03) 



EXPERIMENTAL INVESTIGATION OF SCREECHING 
COMBUSTION IN FULL-SCALE AFTERBURNER. 
Karl H. Usow, Carl L. Meyer, and Frederick W. 
Schulze. December 1953. 62p. diagrs., photos., 
tab. (NACA RM E53I01) 



HIGH-ALTITUDE PERFORMANCE OF 9.5-INCH- 
DIAMETER TUBULAR EXPERIMENTAL COMBUS- 
TOR WITH FUEL STAGING, Wilfred E. Scull. 
March 1954. 55p. diagrs., photos., tabs 
(NACA RM E54A06) 



A SUMMARY OF PRELIMINARY INVESTIGATIONS 
INTO THE CHARACTERISTICS OF COMBUSTION 
SCREECH IN DUCTED BURNERS. Lewis Labora- 
tory Staff. April 1954. 80p. diagrs., photos. 
(NACARME54B02) 



SOME SCREE CHIN G- COMBUSTION CHARACTER- 
ISTICS OF A TRANSPIRATION -COOLED AFTER- 
BURNER HAVING A POROUS WALL OF WIRE 
CLOTH. William K. Koffel, James L. Harp, Jr., 
and Lively Bryant. November 1954. 12p. diagrs. 
(NACA RM E54H27) 



218 



(31 PROPULSION 



PHOTOGRAPHIC INVESTIGATION OF AIR -FLOW 
PATTERNS IN TRANSPARENT ONE -SIXTH SECTOR 
OF. ANNULAR TURBOJET-ENGINE COMBUSTOR 
WITH AXIAL-SLOT -TYPE AIR ADMISSION. 
Charles C Graves and J. DeanGernon. December 
1954. 24p. diagrs., photos. (NAC A RM E 54128a) 



EFFECTIVENESS OF A TURBOJET TUBULAR 
COMBUSTOR IN SCREENING THE TURBINE FROM 
FOREIGN OBJECTS. Patrick T. Chiarito. July 
1955. 20p. diagrs., photos. (NACA RM E55E16) 



EFFECTS OF INLET-AIR-FLOW DISTORTION ON 
STEADY -STATE ALTITUDE PERFORMANCE OF AN 
AXIAL-FLOW TURBOJET ENGINE . William 
Conrad, Morgan P. Hanson, and John E. McAulay. 
September 1955. 47p. diagrs., photo. 
(NACARM E55A04) 



ANALYTICAL AND EXPERIMENTAL STUDY OF 
TRANSIENT -RESPONSE CHARACTERISTICS OF A 
TURBOPROP ENGINE. R. T. Craig, S- Nakanishi, 
and D. B. Wile. October 1955. 50p. diagrs., photo., 
tabs. (NACARM E55C23) 



EXPLORATORY INVESTIGATION OF A HELICOP- 
TER PRESSURE-JET SYSTEM ON THE LANGLEY 
HELICOPTER TEST TOWER. Robert A. Makofski 
and James P. Shivers. July 1956. 38p. diagrs., 
photo. (NACA RM L56B17) 



SPONTANEOUS IGNITION OF PENTABORANE 
SPRAYS IN A HOT-AIR STREAM. Erwin A. Lezberg 
and Albert M. Lord. November 1956. 26p. diagrs. 
(NACA RM E55F29a) 



DROP BURNING RATES OF HYDROCARBON AND 
NONHYDROCARBON FUELS. Arthur L. Smith and 
Charles C. Graves. August 1957. 22p. diagrs., 
photos., tabs. (NACA RM E57F11) 

SUMMARY OF NACA RESEARCH ON IGNITION LAG 
OF SELF-IGNITING FUEL - NITRIC ACID PRO- 
PELLANTS. Gerald Morrell. October 1957. 48p. 
diagrs., photos., tabs. (NACA RM E57G19) 

EFFECT OF INITIAL MDCTURE -TEMPERATURE ON 
BURNING VELOCITY OF HYDROGEN-AIR MA- 
TURES WITH PREHEATING AND SIMULATED 
PREBURNING. Sheldon Heimel. October 1957. 
23p. diagrs., tabs. (NACA TN 4156) 



(3.5.2.2) 
TURBINE ENGINES 



ANALYTICAL AND EXPERIMENTAL INVESTIGA- 
TION OF THRUST AUGMENTATION OF AXIAL- 
AND CENTRIFUGAL-COMPRESSOR TURBOJET 
ENGINES BY INJECTION OF WATER AND ALCO- 
HOL IN COMBUSTION CHAMBERS. David S. 
Gabriel, Harry W, Dowman, and William L. Jones. 
April 13, 1950. 43p. diagrs., photo. 
(NACA RM E9K29) 



NACA RESEARCH ON COMBUSTORS FOR AIR- 
CRAFT GAS TURBrNES. I - EFFECT OF OPER- 
ATING VARIABLES ON STEADY-STATE PERFORM- 
ANCE. Walter T. Olson and J. Howard Childs. 
October 18, 1950. 55p. diagrs., tab. 
(NACA RM E50H31) 



TURBOJET COMBUSTOR EFFICIENCY AT HIGH 
ALTITUDES. Walter T. Olson, J. Howard Childs, 
and Edmund R. Jonash. October 27, 1950. 51p. 
diagrs., photo. (NACA RM E50I07) 



VAPOR-FUEL-DISTRIBUTION EFFECTS ON COM- 
BUSTION PERFORMANCE OF A SINGLE TUBULAR 
COMBUSTOR. Richard J. McCafferty. 
December 13, 1950. 27p. diagrs., photo. 
(NACA RM E50JO3) 



INVESTIGATION OF ALTITUDE IGNITION, ACCEL- 
ERATION AND STEADY-STATE OPERATION WITH 
SINGLE COMBUSTOR OF J47 TURBOJET ENGINE. 
William P. Cook and Helmut F. Butze. March 5, 
1951. 35p. diagrs., photo., tab. 
(NACARME51A25) 



LIQUID-FUEL-DISTRIBUTION AND FUEL-STATE 
EFFECTS ON COMBUSTION PERFORMANCE OF A 
SINGLE TUBULAR COMBUSTOR . Richard J . 
McCafferty. May 1, 1951. 38p. diagrs., tab. 
(NACARME51B21) 



COMBUSTION EFFICIENCY PERFORMANCE OF A 
MIL-F-5624 TYPE FUEL AND MONOMETHYL- 
NAPHTHALENE IN A SINGLE VAPORIZING-TYPE 
COMBUSTOR. Anthony W. Jones and William P. 
Cook. February 1952. 26p. diagrs., photos., tabs. 
(NACARME51K30) 



ALTITUDE PERFORMANCE INVESTIGATION OF 
TWO FLAME-HOLDER AND FUEL-SYSTEM CON- 
FIGURATIONS IN SHORT AFTERBURNER. S. C. 
Huntley and H. D. Wilsted. May 1952. 41p. 
diagrs., photos., tab. (NACARM E52B25) 



ALTITUDE PERFORMANCE INVESTIGATION OF 
SINGLE- AND DOUBLE -ANNULAR TURBOJET - 
ENGINE COMBUSTORS WITH VARIOUS SIZE FUEL 
NOZZLES. James L. Harp, Jr., and Kenneth R. 
Vincent. June 1952. 60p. photos., diagrs., tab. 
(NACA RM E51L14) 



COMPONENT AND OVER -ALL PERFORMANCE 
EVALUATION OF AN AXIAL-FLOW TURBOJET 
ENGINE OVER A RANGE OF ENGINE -INLET 
REYNOLDS NUMBERS. Curtis L. Walker, S- C. 
Huntley, andW. M. Braithwaite. July 1952. 42p. 
diagrs., tabs. (NACA RM E52B08) 



EFFECT OF WATER VAPOR ON COMBUSTION OF 

MAGNESIUM -HYDROCARBON SLURRY FUELS IN 
SMALL-SCALE AFTERBURNER. Leonard K. 
Tower. October 1952. 39p. diagrs., tabs. 
(NACARM E52H25) 



TURBOJET COMBUSTOR EFFICIENCY WITH 
CERAMIC -COATED LINERS AND WITH MECHANI- 
CAL CONTROL OF FUEL WASH ON WALLS. 
Helmut F. Butze and Edmund R. Jonash. November 
1952. 43p. photos., diagrs., tabs. 
(NACA RM E52I25) 



ALTITUDE STARTING CHARACTERISTICS OF AN 
AFTERBURNER WITH AUTOIGNITION AND HOT- 
STREAK IGNITION. P. E. Renas, R. W. Harvey, 
Sr., and E. T. Jansen. April 1953. 25p. diagrs., 
photos., tab. (NACA RM E53B02) 



ALTITUDE PERFORMANCE INVESTIGATION OF 
TWO SINGLE -ANNULAR TYPE COMBUSTORS AND 
THE PROTOTYPE J40-WE-8 TURBOJET ENGINE 
COMBUSTOR WITH VARIOUS COMBUSTOR INLET- 
AIR PRESSURE PROFILES, Adam E. Sobolewski, 
Robert R. Miller, and John E. McAulay. May 1953. 
46p. diagrs., photos., tab. (NACA RM E52J07) 



(3) PROPULSION 



219 



ALUMINUM BOROHYDRIDE AS AN IGNITION 
SOURCE FOR TURBOJET COMBUSTORS. David M. 
Straight, Edward A. Fletcher, and Hampton H. 
Foster. September 1953. 19p. diaera.. photos., 
tabs. (NACA RM E53G15) 



PRELIMINARY INVESTIGATION OF AN ANNULAR 
TURBOJET COMBUSTOR HAVING A CATALYTIC- 
COATED LINER. Carl T. NorgrenandJ. Howard 
Childs. January 1954. lip. diagrs. (NACA 
RM E53L07) 



HIGH -ALTITUDE PERFORMANCE OF 9. 5-INCH - 
DIAMETER TUBULAR EXPERIMENTAL COMBUS- 
TOR WITH FUEL STAGING. Wilfred E. Scull. 
March 1954. 55p. diagrs., photos., tabs. 
(NACA RM E54A06) 



LOW-PRESSURE PERFORMANCE OF EXPERIMEN- 
TAL PREVAPORIZING TUBULAR COMBUSTOR 
USING APPROXIMATELY STOICHIOMETRIC AD- 
MISSION OF FUEL-AIR MIXTURE INTO THE PRI- 
MARY ZONE. Robert R. Hlbbard, Allen J. Metzler, 
and Wilfred E. Scull. August 1954. 38p. diagrs., 
tabs. (NACA RM E54F25a) 



PERFORMANCE OF A PAIR OF TUBULAR COMBUS- 
TORS WITH AN EXTERNAL PILOT CHAMBER. 
Robert Friedman and Eugene V. Zettle. September 
1954. 26p. diagrs., tab. (NACA RM E54EU) 



PHOTOGRAPHIC INVESTIGATION OF AIR-FLOW 
PATTERNS IN TRANSPARENT ONE-SIXTH SECTOR 
OF ANNULAR TURBOJET -ENGINE COMBUSTOR 
WITH AXIAL-SLOT -TYPE AIR ADMISSION. 
Charles C. Graves and J. DeanGernon. December 
1954. 24p. diagrs., photos. (NACA RM E 54128a) 



ALUMINUM BOROHYDRIDE - HYDROCARBON MIX- 
TURES AS A SOURCE OF IGNITION FOR A TURBO- 
JET COMBUSTOR. Hampton H. Foster, Edward A. 
Fletcher, and David M. Straight. February 1955. 
24 p. diagrs., photo., tabs. (NACA RM E54K12) 



MODIFIED TUBULAR COMBUSTORS AS HIGH- 
TEMPERATURE GAS GENERATORS. Robert 
Friedman and Eugene V. Zettle. October 1955. 
17p. diagrs., photos., tabs. (NACA RM E55H25) 



FACTORS THAT AFFECT OPERATIONAL RELI- 
ABILITY OF TURBOJET ENGINES. Lewis 
Laboratory Staff. January 1956. 376p. diagrs., 
photos., tabs. (NACA RM E55H02) 



BASIC CONSIDERATIONS IN THE COMBUSTION OF 
HYDROCARBON FUELS WITH AIR. Propulsion 
Chemistry Division. Edited by Henry C. Barnett and 
Robert R. Hibbard. Chap. I: ATOMIZATION AND 
EVAPORATION OF LIQUID FUELS. Charles C. 
Graves and Donald W. Bahr. Chap. II: FLOW AND 
MIXING PROCESSES IN COMBUSTION CHAMBERS. 
Wilfred E. Scull and William R. Mickelsen. 
Chap. HI: IGNITION AND FLAMMABILITY OF 
HYDROCARBON FUELS. Frank E. Belles and 
Clyde C. Swett. Chap. IV: LAMINAR FLAME 
PROPAGATION. Gordon L. Dugger, Dorothy M. 
Simon, and Melvin Gerstein. Chap. V: TURBU- 
LENT FLAMES. Melvin Gerstein and Gordon L. 
Dugger. Chap. VI: FLAME STABILIZATION. 
Gordon L. Dugger and Melvin Gerstein. Chap. VII: 
DIFFUSION FLAMES. Richard S. Brokaw and 
Melvin Gerstein. Chap. VD3: OSCILLATIONS IN 
COMBUSTORS. Perry L. Blackshear, Jr., and 
Warren D. Rayle. Chap. IX : SMOKE AND COKE 
FORMATION IN THE COMBUSTION OF 
HYDROCARBON-AIR MDCTURES. Rose L. Schalla 
and Robert R. Hibbard. 1957. xi, 259p. diagrs., 
photos., tabs. (NACA Rept. 1300) 



RELATION OF TURBOJET AND RAMJET COMBUS- 
TION EFFICIENCY TO SECOND-ORDER REACTION 
KINETICS AND FUNDAMENTAL FLAME SPEED. 
J. Howard Childs, Thaine W. Reynolds, and Charles 
C. Graves. 1957. ii, 13p. diagrs. 
(NACA Rept. 1334) 



INVESTIGATION OF 70 PERCENT TRIMETHYL 
BORATE - 30 PERCENT METHYL ALCOHOL FUEL 
MIXTURE IN A SINGLE J33 COMBUSTOR AND IN A 
J33 TURBOJET ENGINE. Louis J. Schafer, Jr., 
and Robert 0. Hickel. January 1957. 26p. diagrs. , 
photos., tab. (NACA RM E53C24) 



PERFORMANCE OF AN EXPERIMENTAL ANNULAR 
TURBOJET COMBUSTOR WITH METHANE AND 
PROPANE. Carl T. Norgren. January 1957. 27p. 
diagrs., tabs. (NACA RM E56J22) 



EFFECT OF FUEL VARIABLES ON CARBON FOR- 
MATION IN TURBOJET-ENGINE COMBUSTORS. 
Edmund R. Jonash, Jerrold D. Wear, and William P. 
Cook. 1958. ii, 18p. diagrs., photos., tabs. 
(NACA Rept. 1352. Supersedes RM E52G11, 
RM E52H21, RM E53D15, RM E54H23, RM E55D28, 
RME55F30a, RM E55J31) 



(3.5.2.3) 
RAM-JET ENGINES 



INVESTIGATION OF EFFECTS OF SEVERAL FUEL- 
INJECTION LOCATIONS ON OPERATIONAL PER- 
FORMANCE OF A 20-INCH RAM JET. W. H. 
Sterbentz, E Perchonok, and F. A. Wilcox. 
Junu 8, 1948. 39p. diagrs., photos. 
(NACA RM E7L02) 



INVESTIGATION OF COMBUSTION IN 16 -INCH RAM 
JET UNDER SIMULATED CONDITIONS OF HIGH 
ALTITUDE AND HIGH MACH NUMBER. T.J. 
Nussdorfer, D. C. Seder Strom, andE. Perchonok. 
June 27, 1950. 53p. diagrs., photos., tabs. 
(NACARM E50D04) 



ALTITUDE-TEST-CHAMBER INVESTIGATION OF 
PERFORMANCE OF A 28-INCH RAM -JET ENGINE. 
I - COMBUSTION AND OPERATIONAL PERFORM- 
ANCE OF FOUR COMBUSTION -CHAMBER CONFIG- 
URATIONS. W. L. Jont-s, T. B. Shillito, and J. G. 
Henzel, Jr. August 23, 1950. 53p. diagrs., photos. 
(NACA RM E50F16) 



ALTITUDE -TEST -CHAMBER INVESTIGATION OF 
PERFORMANCE OF A 28-INCH RAM -JET ENGINE. 
H - EFFECTS OF GUTTER WIDTH AND BLOCKED 
AREA ON OPERATING RANGE AND COMBUSTION 
EFFICIENCY. T. B. Shillito, W. L. Jones, and 
R. W. Kahn. November 6, 1950. 58p. diagrs. 
(NACA RM E50H21) 



ALTITUDE-TEST-CHAMBER INVESTIGATION OF 
PERFORMANCE OF A 28 -INCH RAM -JET ENGINE. 
Ill - COMBUSTION AND OPERATIONAL PERFORM- 
ANCE OF THREE FLAME HOLDERS WITH A CEN- 
TER PILOT BURNER. Thomas B. Shillito, George 
G. Younger, and James G. Henze], Jr. February 6, 
1951. 30p. diagrs. (NACA RM E50J20) 



INTERNAL FLOW AND BURNING CHARACTERIS- 
TICS OF 16-INCH RAM JET OPERATING IN A FREE 
JET AT MACH NUMBKRS OF 1.35 AND 1.73, 
Eugene Perch'. nek and J.;hn M. Farley. May 21, 
1951. 37p. dingrs., phut s., tab. 
(NACA RM E51C16) 



220 



(3) PROPULSION 



altitude -test-chamber investigation of 
performance of a 28-inch ram-jet engine. 
iv - effect of inlet-air temperature, 
Combustion -chamber-inlet mach number, 
and fuel volatility on combustion per- 
FORMANCE. Robert W. Kahn, Shigeo Nakanishi, 
and James L. Harp, Jr. July 1951. 27p. diagrs. 
(NACA RM E51D11) 



EFFECT OF WATER VAPOR ON COMBUSTION OF 
MAGNESIUM-HYDROCARBON SLURRY FUELS IN 
SMALL-SCALE AFTERBURNER. Leonard K. 
Tower. October 1952. 39p. diagrs., tabs. 
(NACA RM E52H25) 



PRELIMINARY EXPERIMENTS WITH PILOT BURN- 
ERS FOR RAM -JET COMBUSTORS. John M. 
Farley, Robert E. Smith, and John H. Povolny. 
January 1953. 45p. diagrs., photos., tabs. 
(NACARM E52J23) 



EFFECT OF FUEL-AIR RATIO CONCENTRATION 
IN COMBUSTION ZONE ON COMBUSTION PER- 
FORMANCE OF A 16-INCH RAM-JET ENGINE. 
A. J. Cervenka, D. W. Bahr, andE. E. Dangle. 
April 1953. 24p. diagrs., tab. 
(NACARM E53BI9) 



FREE -JET ALTITUDE INVESTIGATION OF A 20- 
INCH RAM -JET COMBUSTOR WITH A RICH INNER 
ZONE OF COMBUSTION FOR IMPROVED LOW- 
TEMPERATURE -RATIO OPERATION. Arthur M. 
Trout and Carl B. Wentworth. May 1953. 28p. 
diagrs., photo (NACA RM E52L26) 



EFFECT OF FUEL INJECTOR LOCATION AND 
MIXTURE CONTROL ON PERFORMANCE OF A 
16-INCH RAM-JET CAN -TYPE COMBUSTOR. 
A. J. Cervenka, Eugene Perchonok, and E. E. 
Dangle. July 1953. 33p. diagrs., tab. (NACA 
RM E53F15) 



ENGINEERING METHOD OF RAM -JET THRUST 
DETERMINATION BASED ON EXPERIMENTALLY 
OBTAINED COMBUSTOR PARAMETERS. 
H. Rudolph Dettwyler and Maxime A. Faget. August 
1953. 44p. diagrs., tab. (NACA RM L53E21) 



EFFECT OF INLET-AIR TEMPERATURE ON PER- 
FORMANCE OF A 16-INCH RAM-JET COMBUSTOR. 
A. J. Cervenka, E. E. Dangle, and Robert 
Friedman. October 1953. 24p. diagrs., tab. 
(NACA RM E53I03) 



EFFECT OF MECHANICALLY INDUCED SINUSOIDAL 
AIR-FLOW OSCILLATIONS ON OPERATION OF A 
RAM-JET ENGINE. E. E. Dangle, A. J. Cervenka, 
and Eugene Perchonok. June 1954. 24p. diagrs., 
tab. (NACA RM E54D01) 



PERFORMANCE OF A 16-INCH RAM-JET ENGINE 
WITH A CAN-TYPE COMBUSTOR AT MACH NUM- 
BERS OF 1.50 TO 2.16. Donald P. Hearth and 
Eugene Perchonok. August 1954. 30p. diagrs. 
(NACA RM F.54G13) 



FLIGHT AND PRE FLIGHT TESTS OF A RAM JET 
BURNING MAGNESIUM SLURRY FUEL AND 
UTILIZING A SOLID-PROP ELLANT GAS GENERA- 
TOR FOR FUEL EXPULSION. Walter A. Bartlett, 
Jr., and William K. Hagginbothom, Jr. April 1955. 
35p. diagrs., photos. (NACA RM L55A24) 



EXPERIMENTAL EVALUATION OF BORON- 
HYDROCARBON SLURRY IN A 16-INCH RAM-JET 
COMBUSTOR. William R. Ker slake, E. E. Dangle, 
and A. J. Cervenka. June 1955. 37p. diagrs., 
photos., tabs. (NACA RM E55C07) 



PREFLIGHT AND FLIGHT-TEST INVESTIGATION 
OF A 50-PERCENT-MAGNESIUM 50-PERCENT 
JP-4 SLURRY FUEL IN A TWIN-ENGINE RAM -JET 
VEHICLE. Otto F. Trout, Jr., and Thomas L. 
Kennedy. May 1956. 27 p. diagrs., photos. 
(NACA RM L56C06) 



BASIC CONSIDERATIONS IN THE COMBUSTION OF 
HYDROCARBON FUELS WITH AIR. Propulsion 
Chemistry Division . Edited by Henry C . Barnett and 
Robert R. Hibbard. Chap. I: ATOMIZATION AND 
EVAPORATION OF LIQUID FUELS. Charles C. 
Graves and Donald W. Bahr. Chap. II: FLOW AND 
MIXING PROCESSES IN COMBUSTION CHAMBERS. 
Wilfred E. Scull and William R. Mickelsen. 
Chap. HI: IGNITION AND FLAMMABBLITY OF 
HYDROCARBON FUELS. Frank E. Belles and 
Clyde C. Swett. Chap. IV: LAMINAR FLAME 
PROPAGATION. Gordon L. Dugger, Dorothy M. 
Simon, and Melvin Gerstein. Chap. V: TURBU- 
LENT FLAMES. Melvin Gerstein and Gordon L. 
Dugger. Chap. VI: FLAME STABILIZATION. 
Gordon L. Dugger and Melvin Gerstein. Chap. VH: 
DIFFUSION FLAMES. Richard S. Brokaw and 
Melvin Gerstein. Chap. VHI: OSCULATIONS IN 
COMBUSTORS. Perry L. Blackshear. Jr., and 
Warren D. Rayle. Chap. DC: SMOKE AND COKE 
FORMATION IN THE COMBUSTION OF 
HYDROCARBON -AIR MIXTURES. Rose L. SchaUa 
and Robert R. Hibbard. 1957. xi, 2 59p. diagrs., 
photos., tabs. (NACA Rept. 1300) 



RELATION OF TURBOJET AND RAMJET COMBUS- 
TION EFFICIENCY TO SECOND -ORDER REACTION 
KINETICS AND FUNDAMENTAL FLAME SPEED. 
J. Howard Childs, Thaine W. Reynolds, and Charles 
C. Graves. 1957. ii, 13p. diagrs. 
(NACA Rept. 1334) 



FLIGHT INVESTIGATION OF A RAM JET BURNING 
MAGNESIUM SLURRY FUEL AND HAVING A CONI- 
CAL SHOCK INLET DESIGNED FOR A MACH NUM- 
BER OF 4.1. Walter A. Bartlett, Jr., and 
Charles F. Merlet. January 1957. 23 p. diagrs., 
photos. (NACA RM L56I24a) 



PRELIMINARY INVESTIGATION OF PROPANE 
COMBUSTION IN A 3 -INCH-DIAMETER DUCT AT 
INLET-AIR TEMPERATURES OF 1400° TO 1600° F. 
Erwin A. Lezberg. July 1957. 19p. diagrs., 
photos., tab. (NACA TN 4028) 



DROP -SIZE DISTRIBUTION FOR CROSSCURRENT 
BREAKUP OF LIQUID JETS IN AIRS T RE A MS. 
Robert D. Ingebo and Hampton H. Foster. 
October 1857. 36p. diagrs., photos, tabs. 
(NACA TN 4087) 



PRELIMINARY SURVEY OF PROPULSION USING 
CHEMICAL ENERGY STORED IN THE UPPER 
ATMOSPHERE. Lionel V. Baldwin and Perry L. 
Blackshear. Appendix D: HEAT TRANSFER AND 
FRICTION DRAG. James F. Schmidt. May 1958. 
73p. diagrs., tabs. (NACA TN 4267) 



EFFECT Or PRESSURE AND DUCT GEOMETRY ON 
BLUFF-BODY FLAME STABILIZATION. Andrew E. 
Potter, Jr., and Edgar L. Wong. September 1958. 
31p. diagrs., tab. (NACA TN 4381) 



AN ANALYSIS OF RAMJET ENGINES USING SUPER- 
SONIC COMBUSTION. Richard J. Weber and John 
S. MacKay. September 1958. 49p. diagrs., tab. 
(NACA TN4386) 



(3) PROPULSION 



221 



(3.5.2.5) 
ROCKET ENGINES 



PRELIMINARY INVESTIGATION OF A CHEMICAL 
STARTING TECHNIQUE FOR THE ACID GASOLINE 
ROCKET PROPELLANT SYSTEM. Glen Hennings 
and Gerald Morrell. January 1953. 23p. photo., 
diagrs., tab. (NACA RM E52K21) 



INVESTIGATION OF LIQUID FLUORINE - LIQUID 
AMMONIA PROPELLANT COMBINATION IN A 100- 
POUND-THRUST ROCKET ENGINE. Edward A. 
Rothenberg and Howard W. Douglass. July 1953. 
31p. diagrs., photos., tabs. (NACA RM E53E08) 



PHOTOGRAPHIC STUDY OF ROTARY SCREAMING 
AND OTHER OSCILLATIONS IN A ROCKET ENGINE. 
Theodore Male, William R. Ker slake, and 
AdelbertO. Tischler. May 1954. 37p. diagrs., 
photos. (NACA RM E54A29) 



THEORETICAL PERFORMANCE OF JP-4 FUEL 
WITH A 70-PERCENT-FLUORINE - 30-PERCENT - 
OXYGEN MDCTURE AS A ROCKET PROPELLANT. 
I - FROZEN COMPOSITION. Sanford Gordon and 
Vearl N. Huff. April 1956. 38p. diagrs., tabs. 
(NACA RM E56A13a) 



A STUDY OF FUEL-NITRIC ACID REACTTVTrY. 
Charles E. FeUer and Louis Baker, Jr. April 1956. 
48p. diagrs., photo., tabs. (NACA RM E 56 A 19) 



EFFECT OF FUELS ON SCREAMING IN 200- 
POUND-THRUST LIQUID-OXYGEN - FUEL ROCKET 
ENGINE. Isaac Pass and Adelbert O. Tischler. 
June 1956. 25p. diagrs., photos., tab. 
(NACA RM E56C10) 



INJECTION PRINCIPLES FOR LIQUID OXYGEN AND 
HEPTANE USING TWO-ELEMENT INJECTORS. 
Marcus F. Heidmann. June 1956. 30p. diagrs., 
photos., tab. (NACARM E56D04) 



THEORETICAL PERFORMANCE OF JP-4 FUEL 
WITH A 70-30 MIXTURE OF FLUORINE AND 
OXYGEN AS A ROCKET PROPELLANT. II - EQUI- 
LIBRIUM COMPOSITION. Sanford Gordon and Vearl 
N. Huff. October 1956. 49p. diagrs., tabs. 
(NACARME56F04) 



EFFECTS OF VARIATIONS IN COMBUSTION- 
CHAMBER CONFIGURATION ON IGNITION DELAY 
IN A 50-POUND-THRUST ROCKET. Dezso J. - 
Ladanyi. October 1956. 53p. diagrs., photos., tabs. 
(NACA RM E56F22) 



A STUDY OF INJECTION PROCESSES FOR LIQUID 
OXYGEN AND GASEOUS HYDROGEN IN A 200- 
POUND-THRUST ROCKET ENGINE. Carmon M. 
Auble. January 1957. 32p. diagrs., photos. - 
(NACA RM E 56125a) 



PROPELLANT VAPORIZATION AS A CRITERION 
FOR ROCKET-ENGINE DESIGN; EXPERIMENTAL 
EFFECT OF FUEL TEMPERATURE ON UQUID- 
OXYGEN - HEPTANE PERFORMANCE. M. F. 
Heidmann. July 1957. 21p. diagrs., tabs. 
(NACA RM E57E03) 



INJECTION PRINCIPLES FOR LIQUID OXYGEN AND 
HEPTANE USING NINE-ELEMENT INJECTORS IN 
AN 1800-POUND-THRUST ROCKET ENGINE. 
Richard F- Neu. July 1957. 27p. diagrs., photos., 
tab (NACA RM E57E13) 



PROPELLANT VAPORIZATION A3 A CRITERION 
FOR ROCKET ENGINE DESIGN; CALCULATIONS 
OF CHAMBER LENGTH TO VAPORIZE A SINGLE 
n-HEPTANE DROP. Richard J. Priem. July 1957. 
41p. diagrs.. tab. (NACA TN 3985} 



SUMMARY OF NACA RESEARCH ON IGNITION LAG 
OF SELF-IGNITING FUEL - NITRIC ACID PRO- 
PELLANTS. Gerald Morrell. October 1957. 48p. 
diagrs., photos., tabs. (NACA RM E57G19) 



PROPELLANT VAPORIZATION AS A CRITERION 
FOR ROCKET -ENGINE DESIGN; CALCULATIONS 
USING VARIOUS LOG -PROBABILITY DISTRIBU- 
TIONS OF HEPTANE DROPS. Richard J. Priem. 
October 1957. 29p. diagrs., tab. (NACA TN 4098) 



THEORETICAL ROCKET PERFORMANCE OF 
JP-4 FUEL WITH SEVERAL FLUORINE -OXYGEN 
MIXTURES ASSUMING FROZEN COMPOSITION. 
Sanford Gordon and Kenneth S. Drellishak. 
November 1957. 62p. diagrs. , tabs. 
(NACA RM E57G16a) 



EFFECT OF FUEL-ORIFICE DIAMETER ON PER- 
FORMANCE OF HEPTANE-OXYGEN ROCKET . 
ENGINES. Richard J. Priem and Martin Hersch. 
February 1958. 20p. diagrs. (NACA RM E57I26) 



THEORETICAL ROCKET PERFORMANCE OF JP-4 
FuEL WITH SEVERAL FLUORINE -OXYGEN MIX- 
TURES ASSUMING EQUILIBRIUM COMPOSITION. 
Sanford Gordon. February 1958. 69p. diagrs., 
tabs. (NACA RM E57K22) 



PROPELLANT VAPORIZATION AS A CRITERION 
FOR ROCKET ENGINE DESIGN; RELATION BE- 
TWEEN PERCENTAGE OF PROPELLANT VAPOR- 
IZED AND ENGINE PERFORMANCE. Marcus F. 
Heidmann and Richard J. Priem. March 1958. 
19p. diagrs. (NACA TN 4219) 



DROP -SIZE DISTRIBUTIONS FOR IMPINGING-JET 
BREAKUP IN AIRSTREAMS SIMULATING THE 
VELOCITY CONDITIONS IN ROCKET COMBUSTORS. 
Robert D. Ingebo. March 1958. 23p. diagrs 
photos., tab. (NACA TN 4222) 



THEORETICAL PERFORMANCE OF LIQUID AMMO- 
NIA WITH LIQUID OXYGEN AS A ROCKET PROPEL- 
LANT. Sanford Gordon and Alan R. Glueck. May 
1958. 84p. diagrs., tabs. (NACARM E58A21) 



THEORETICAL ROCKET PERFORMANCE OF 
LIQUID METHANE WITH SEVERAL FLUORINE- 
OXYGEN MDCTURES ASSUMING FROZEN COMPOSI- 
TION. Sanford Gordon and Michael E. Kastner. 
May 1958. 44p. diagrs., tabs. (NACA RM E58B20) 



EFFECT OF FUEL DROP SIZE AND INJECTOR 
CONFIGURATION ON SCREAMING IN A 200-POUND- 
THRUST ROCKET ENGINE USING LIQUID OXYGEN 
AND HEPTANE. Charles E. Feiler. June 1958. 
27p. diagrs., photos., tab. (NACA RM E58A20af 



SCREAMING TENDENCY OF THE GASEOUS- 
HYDROGEN - LIQUID-OXYGEN PROPELLANT 
COMBINATION. Louis Baker, Jr., and Fred W. 
Steffen. September 1958. 24p. diagrs., photos., 
tabs. (NACA RM E58E09) 



COMBUSTOR PERFORMANCE WITH VARIOUS 
HYDROGEN-OXYGEN INJECTION METHODS IN A 
200-POUND-THRUST ROCKET ENGINE. M. F., 
Heidmann and Louis Baker, Jr. September 1958. 
45p. diagrs., photos., tab. (NACA RM E58E21) 



222 



(3) PROPULSION 



PROPELLANT VAPORIZATION AS A CRITERION 

FOR ROCKET-ENGINE DESIGN; CALCULATIONS 
OF CHAMBER LENGTH TO VAPORIZE VARIOUS 
PRCPELLANTS. Richard J. Priem. September 
1958. 36p. diagrs., tab. (NACA TN 3883) 



AN ANALYTICAL STUDY OF TURBULENT AND 
MOLECULAR MIXING IN ROCKET COMBUSTION. 
David A. Bittker. September 1958. 22p. diagrs. 
(NACA TN 4321) 



A MACH 4 ROCKET-POWERED SUPERSONIC TUN- 
NEL USING AMMONIA -OXYGEN AS WORKING 
FLUID. Robert W. Graham, Eleanor Costilow 
Guentert, and Vearl N. Huff. September 1958. 53p. 
diagrs., photos. (NACA TN 4325) 



(3) PROPULSION 



223 



(3.6) 
Compression and Compressors 



DESIGN AND TEST OF MIXED- FLO*' IMPELLERS. 
HI - DESIGN AND EXPERIMENTAL RESULTS FOR 
IMPELLER MODEL MFI-2A AND COMPARISON 
WITH IMPELLER MODEL MFI-1A. Joseph T. 
Hamrick, Walter M. Osborn, and William L. Beede. 
March 1953. 34 p. diagrs., photo., tab. 
(NACA RM E52L22a) 



DESIGN AND TEST OF MIXED- FLOW IMPELLERS. 
IV - EXPERIMENTAL RESULTS FOR IMPELLER 
MODELS MFI-1 AND MFI-2 WITH CHANGES IN 
BLADE HEIGHT. Joseph T. Hamrick, William L. 
Beede, and Joseph R. Withee, Jr. February 1954. 
32p. diagrs., photos. (NACA RM E53L02) 



PERFORMANCE OF MIXED-FLOW IMPELLER, 
MODEL MFI-1B, WITH DIFFUSER VANES AT 
EQUIVALENT IMPELLER SPEEDS FROM 1100 TO 
1700 FEET PER SECOND. Walter M. Osborn. 
June 1954. 16p. diagrs., photo. 
(NACA RM E54D23) 



THROAT -AREA DETERMINATION FOR A CASCADE 
OF DOUBLE -CIRCULAR -ARC BLADES. Linwood 
C. Wright and Richard Schwind. November 1955. 
20p. diagrs. (NACA RM E55H25a) 



PRELIMINARY ATTEMPTS AT ISOTHERMAL COM- 
PRESSION OF A SUPERSONIC AIR STREAM. 
E. Perchonok and F. Wilcox. January 1956. 33p. 
diagrs., photos., lab. (NACA RM E 5 51 2 9 a) 



DESIGN AND TEST OF MDCED-FLOW IMPELLERS. 
VIII - COMPARISON OF EXPERIMENTAL RESULTS 
FOR THREE IMPELLERS WITH SHROUD REDE- 
SIGNED BY RAPID APPROXIMATE METHOD. 
Walter M. Osborn, Kenneth J. Smith, and Joseph T. 
Hamrick. February 1957. 32p. diagrs., photos. 
(NACA RM E56L07) 



(3.6.1) 

FLOW THEORY AND 

EXPERIMENT 



EXPERIMENTAL INVESTIGATION OF A 16 -INCH 
IMPULSE-TYPE SUPERSONIC -COMPRESSOR 
ROTOR. Guy N. UUman, Melvin J. Hartmann, and 
Edward R. Tysl. October 1951. 29p. diagrs., 
photos. (NACA RM E51G19) 



INVESTIGATION OF A 24-INCH SHOCK-IN-ROTOR 
TYPE SUPERSONIC COMPRESSOR DESIGNED FOR 
SIMPLE RADIAL EQUILIBRIUM BEHIND NORMAL 
SHOCK. Harold Lown and Melvin J. Hartmann. 
December 1951. 25 p. diagrs., photo. 
(NACA RM E51H08) 



PERFORMANCE OF A SWEPT LEADING EDGE 
ROTOR OF THE SUPERSONIC TYPE WITH MDCED 
FLOW. Arthur W. Goldstein and Ralph L. Schacht. 
January 1953. 34p. diagrs., photo., tab. 
(NACARM E52K03) 



DESIGN AND TEST OF MIXED -FLOW IMPELLERS. 
m - DESIGN AND EXPERIMENTAL RESULTS FOR 
IMPELLER MODEL MFI-2A AND COMPARISON 
WITH IMPELLER MODEL MFI-1A. Joseph T. 
Hamrick, Walter M. Osborn, and William L. Beede. 
March 1953. 34 p. diagrs., photo., tab. 
(NACA RM E52L22a) 



DESIGN PROCEDURE AND LIMITED TEST RE- 
SULTS FOR A HIGH SOLIDITY, 12-INCH TRAN- 
SONIC IMPELLER WITH AXIAL DISCHARGE. 
Linwood C. Wright and Karl Kovach. April 1953. 
37p. photos., diagrs., tab. (NACARM E53B09) 



INVESTIGATION OF A 10-STAGE SUBSONIC AXIAL- 
FLOW RESEARCH COMPRESSOR, in - INVESTI- 
GATION OF ROTATING STALL, BLADE VIBRATION, 
AND SURGE AT LOW AND INTERMEDIATE COM- 
PRESSOR SPEEDS. Merle C. Huppert, Eleanor L. 
Costllov, and Ray E. Budlnger. May 1953. 47p. 
diagrs., photos., tabs. (NACA RM E53C19) 



DIFFUSION FACTOR FOR ESTIMATING LOSSES 
AND LIMITING BLADE LOADINGS IN AXIAL- 
FLOW-COMPRESSOR BLADE ELEMENTS. 
Seymour Lieblein, Francis C. Schwenk, and Robert 
L. B rode rick. June 1953. 43p. diagrs., tabs. 
(NACA RM E53D01) 



INVESTIGATION OF 16-INCH IMPULSE-TYPE 
SUPERSONIC COMPRESSOR WITH ROTOR TURN- 
ING PAST AXIAL DIRECTION. John J. Jacklilrh, 
Jr., and Melvin J. Hartmann. July 1953. ?9p. 
dinprs., photos. (NACA RM E53D13) 



INVESTIGATION OF A SUPERSONIC-COMPRESSOR 
ROTOR WITH TURNING TO AXIAL DIRECTION. I - 
ROTOR DESIGN AND PERFORMANCE. Edward R. 
Tysl, John F. Klapproth, and Melvin J. Hartmann. 
August 1953. 36p. diagrs., photos. 
(NACA RM E53F23) 



UTILIZATION OF EXTERNAL-COMPRESSION DIF- 
FUSION PRINCIPLE IN DESIGN OF SHOCK-IN- 
ROTOR SUPERSONIC COMPRESSOR BLADING. 
John W. R. Creagh and John F. Klapproth. 
September 1953. 37p. diagrs., photos., tab. 
(NACARME53F18) 



EXPERIMENTAL INVESTIGATION OF AN AXIAL- 
FLOW COMPRESSOR INLET STAGE OPERATING 
AT TRANSONIC RELATIVE INLET MACH NUM- 
BERS, ffl - BLADE-ROW PERFORMANCE OF 
STAGE WITH TRANSONIC ROTOR AND SUBSONIC 
STATOR AT CORRECTED TIP SPEEDS OF 800 AND 
10OO FEET PER SECOND. Francis C. Schwenk, 
Seymour Lieblein, and George W. Lewis, Jr. 
September 1953. 69p. diagrs., photos., tabs. 
(NACA RM E53G17) 



PERFORMANCE OF A SUPERSONIC MDCED-FLOW 
ROTOR WITH A SWEPT LEADING EDGE AND 0.52 
INLET RADIUS RATIO. Arthur W. Goldstein and 
Ralph L. Schacht. November 1953. 34p. diagrs., 
photos., tab. (NACA RM E53H27) 



224 



(3) PROPULSION 



DESIGN AND TEST OF MIXED-FLOW IMPELLERS 
rV - EXPERIMENTAL RESULTS FOR IMPELLER 
MODELS MFI-1 AND MFI-2 WITH CHANGES IN 
BLADE HEIGHT. Joseph T. Hamrick, William L. 
Beede, and Joseph R. Withee, Jr. February 1954. 
32p. diagrs., photos. (NACA RM E53L02) 



INVESTIGATION OF A SUPERSONIC -COMPRESSOR 
ROTOR WITH TURNING TO AXIAL DIRECTION. 
It - ROTOR COMPONENT OFF -DESIGN AND STAGE 
PERFORMANCE. Melvin J. Hartmann and Edward 
R. Tysl. March 1954. 31p. diagrs., photos. 
(NACA RM E53L24) 



REVIEW OF HIGH-PERFORMANCE AXIAL-FLOW- 
COMPRESSOR BLADE-ELEMENT THEORY. 
Seymour Liebleln. April 1954. 34p. diagrs. 
(NACARM E53L22) 



APPLICATION OF RADIAL-EQUILIBRIUM CONDI- 
TION TO AXIAL-FLOW TURBOMACHINE DESIGN 
INCLUDING CONSIDERATION OF CHANGE OF 
ENTROPY WITH RADIUS DOWNSTREAM OF BLADE 
ROW. James E. Hatch, Charles C. Giamati, and 
Robert J. Jackson. April 1954. 52p. diagrs. 
(NACA RM E54A20) 



PERFORMANCE OF MIXED-FLOW IMPELLER, 
MODEL MFI-1B, WITH DIFFUSER VANES AT 
EQUIVALENT IMPELLER SPEEDS FROM 1100 TO 
1700 FEET PER SECOND. Walter M. Osborn. 
June 1954. 16p. diagrs., photo. 
(NACA RM E54D23) 



INVESTIGATION OF SUPERSONIC-COMPRESSOR 
ROTORS DESIGNED WITH EXTERNAL COMPRES- 
SION. Lawrence J. Jahnsen and Melvin J. 
Hartmann. September 1954. 41p. diagrs., photos. 
(NACA RM E54G27a) 



INVESTIGATION OF COMPRESSIBLE FLOW 
MIXING LOSSES OBTAINED DOWNSTREAM OF A 
BLADE ROW. Warner L. Stewart. December 1954. 
2lp. diagrs, (NACA RM E54I20) 



DESIGN AND PERFORMANCE OF A 1400-FCOT-PER- 
SECOND-TIP -SPEED SUPERSONIC COMPRESSOR 
ROTOR. John F. Klapproth, John J. Jacklitch, Jr., 
and Edward R. Tysl. April 1955. 48p. diagrs., 
photo., tab. (NACA RM E55A27) 



DESIGN AND TEST OF MDCED-FLOW IMPELLERS. 
V - DESIGN PROCEDURE AND PERFORMANCE 
RESULTS FOR TWO VANED DIFFUSERS TESTED 
WITH IMPELLER MODEL MFI-1B. Joseph T. 
Hamrick and Walter M. Osborn. July 1955. 32p. 
diagrs.. photos. (NACA RM E55E13) 



INVESTIGATION OF IMPULSE-TYPE SUPERSONIC 
COMPRESSOR WITH HUB-TIP RATIO OF 0.6 AND 
TURNING TO AXIAL DIRECTION. II - STAGE PER- 
FORMANCE WITH THREE DIFFERENT SETS OF 
STATORS. Ward W. Wilcox. August 1955. 49p. 
diagrs., photos., tab. (NACA RM E55F28) 



DESIGN AND TEST OF MIXED-FLOW IMPELLERS. 
VI - PERFORMANCE OF PARABOLIC -BLADED 
IMPELLER WITH SHROUD REDESIGNED BY RAPID 
APPROXIMATE METHOD. Kenneth J. Smith and 
Walter M. Osborn. September 1955. 22p. diagrs., 
photo., tab. (NACA RM E55F23) 



THROAT-AREA DETERMINATION FOR A CASCADE 
OF DOUBLE-CIRCULAR-ARC BLADES. Linwood 
C. Wright and Richard Schwind. November 1955. 
20p. diagrs. (NACA RM E55H25a) 



PERFORMANCE OF A HIGH-SOLIDITY HIGH- 
PRESSURE-RATIO TRANSONIC ROTOR. Harvey E. 
Neumann. November 1955. 29p. diagrs., photo. 
(NACA RM E55I19) 



DESIGN AND TEST OF MDCED-FLOW IMPELLERS. 
Vn - EXPERIMENTAL RESULTS FOR PARABOLIC - 
BLADED IMPELLER WITH ALTERNATE BLADES 
CUT BACK TO FORM SPLITTER VANES. Walter M. 
Osborn. March 1956. 13p. diagrs., photo. 
(NACA RM E55L15) 



AERODYNAMIC DESIGN OF AXIAL -FLOW COM- 
PRESSORS. VOLUME I. Compressor and Turbine 
Research Division. Edited by Irving A. Johnsen and 
Robert O. Bullock. August 1956. xii, 406p. diagrs., 
photos., tab. {NACA RM E56B03) 



AERODYNAMIC DESIGN OF AXIAL-FLOW COM- 
PRESSORS. VOLUME II. Compressor and Turbine 
Research Division. Edited by Irving A. Johnsen and 
Robert O. Bullock. August 1956. x, 275p. diagrs., 
tabs. (NACA RM E56B03a) 



AERODYNAMIC DESIGN OF AXIAL-FLOW COM- 
PRESSORS. VOLUME III. Compressor and Turbine 
Research Division. Edited by Irving A. Johnsen and 
Robert O. Bullock. August 1956. xii, 364p. diagrs., 
photos., tabs. (NACA RM E56B03b) 



EFFECT OF FLUID-SYSTEM PARAMETERS ON 
STARTING FLOW IN A LIQUID ROCKET. 
Richard P. Krebs. September 1957. 38p. diagrs., 
tab. (NACA TN 4034) 



LOW -SPEED CASCADE INVESTIGATION OF COM- 
PRESSOR BLADES HAVING LOADED LEADING 
EDGES. James C. Emery. January 1958. 76p. 
diagrs., photo., tabs. (NACA TN 4178. Supersedes 
RM L55J05) 



THEORETICAL INVESTIGATION OF SUBSONIC 
OSCILLATORY BLADE -ROW AERODYNAMICS. 
Frank Lane and Manfred Friedman, New York 
University. February 1958. 64p. diagrs., tabs. 
(NACA TN 4136) 



ELLIPTIC FUNCTIONS AND INTEGRALS WITH 
REAL MODULUS IN FLUID MECHANICS. (Les 
Fonctions et Integrates EUiptiques a Module Reel en 
Mecanique des Fluides). Robert Legendre. June 
1958. 113p. diagrs. (NACA TM 1435. Translation 
of Office National d'Etudes et de Recherches 
Aeronautiques, Publication 71, 1954) 



(3.6.1. 1) 
AXIAL FLOW 



ANALYTICAL AND EXPERIMENTAL INVESTIGA- 
TION OF THRUST AUGMENTATION OF AXIAL- 
AND CENTRIFUGAL-COMPRESSOR TURBOJET 
ENGINES BY INJECTION OF WATER AND ALCO- 
HOL IN COMBUSTION CHAMBERS. David S. 
Gabriel, Harry W. Dowman, and William L. Jones. 
April 13, 1950. 43p. diagrs., photo. 
(NACA RM E9K29) 



EXPERIMENTAL INVESTIGATION OF A 16 -INCH 
IMPULSE-TYPE SUPERSONIC -COMPRESSOR 
ROTOR. Guy N. Ullman, Melvin J. Hartmann, and 
Edward R. Tysl. October 1951. 29p. diagrs., 
photos. (NACARM E51G19) 



(3) PROPULSION 



225 



INVESTIGATION OF A 24 -INCH SHOCK -IN -ROTOR 
TYPE SUPERSONIC COMPRESSOR DESIGNED FOR 
SIMPLE RADIAL EQUILIBRIUM BEHIND NORMAL 
SHOCK. Harold Lown and Melvin J. Hartmann. 
December 1S51. 25p. diagrs., photo. 
(N AC ARM E51H08) 



EXPERIMENTAL INVESTIGATION OF AN AXIAL- 
FLOW COMPRESSOR INLET STAGE OPERATING 
AT TRANSONIC RELATIVE INLET MACH NUM- 
BERS. I - OVER- ALL PERFORMANCE OF STAGE 
WITH TRANSONIC ROTOR AND SUBSONIC STATORS 
UP TO ROTOR RELATIVE INLET MACH NUMBER 
OF 1.1. Seymour Lieblein, George W. Lewis, Jr., 
and Donald M. Sandercock. March 1952. 21p. 
diagrs., photos. (NACA RM E52A24) 



INVESTIGATION OF A 10-STAGE SUBSONIC AXIAL- 
FLOW RESEARCH COMPRESSOR- I - AERODY- 
NAMIC DESIGN. Irving A. Johnsen. April 1952. 
41p. diagrs., tabs. (NACA RM E52B18) 



PERFORMANCE OF AN IMPULSE -TYPE SUPER- 
SONIC COMPRESSOR WITH STATORS. John F. 
Klapproth, GuyN. Ullman, and Edward R. Tysl. 
April 1952. 22p. "diagrs., photo. 
(NACA RM E52B22) 



INVESTIGATION OF A 10-STAGE SUBSONIC AXIAL- 
FLOW RESEARCH COMPRESSOR. H - PRELIMI- 
NARY ANALYSIS OF OVER-ALL PERFORMANCE. 
Ray E. Bndinger and Arthur R. Thomson. June 1952. 
23p. diagrs., photos. (NACA RM E52C04) 



EXPERIMENTAL INVESTIGATION OF AXIAL-FLOW 
COMPRESSOR INLET STAGE OPERATING AT 
TRANSONIC RELATIVE INLET MACH NUMBERS, 
n - BLADE -COORDINATE DATA. George W. 
Lewis, Jr. June 1952. 9p. diagrs. 
(NACARME52C27) 



EXPERIMENTAL INVESTIGATION OF AXIAL-FLOW 
COMPRESSOR STATOR BLADES DESIGNED TO 
OBTAIN HIGH TURNING ANGLES BY MEANS OF 
BOUNDARY-LAYER SUCTION. G. R. Costello, 
R. L. Cummings, and G. K. Serovy. June 1952. 
22p. diagrs., photos., tab. (NACA RM E52D18) 



COMPONENT AND OVER -ALL PERFORMANCE 
EVALUATION OF AN AXIAL-FLOW TURBOJET 
ENGINE OVER A RANGE OF ENGINE -INLET 
REYNOLDS NUMBERS. Curtis L. Walker, S. C. 
Huntley, andW. M. Braithwaite. July 1952. 42p. 
diagrs., tabs. (NACA RM E52B08) 



EFFECTS ON THE WEIGHT -FLOW RANGE AND 
EFFICIENCY OF A TYPICAL AXIAL-FLOW COM- 
PRESSOR INLET STAGE THAT RESULT FROM THE 
USE OF A DECREASED BLADE CAMBER OR DE- 
CREASED GUIDE-VANE TURNING. Robert J. 
Jackson. September 1952. 41p. diagrs., photos. 
(NACA RM E52G02) 



DESIGN PROCEDURE AND LIMITED TEST RE- 
SULTS FOR A HIGH SOLIDITY, 12-INCH TRAN- 
SONIC IMPELLER WITH AXIAL DISCHARGE. - 
Linwood C. Wright and Karl Kovach. April 1953. 
37p. photos., diagrs., tab. (NACA RM E53B09) 



INVESTIGATION OF A 10-STAGE SUBSONIC AXIAL- 
FLOW RESEARCH COMPRESSOR. IV - INDIVIDUAL 
STAGE PERFORMANCE CHARACTERISTICS. Ray E. 
Budinger and George K. Serovy. April 1953. 37p. 

diagrs., photo. (NACA RM E53C11) 



INVESTIGATION OF A 10-STAGE SUBSONIC AXIAL- 
FLOW RESEARCH COMPRESSOR. HI - INVESTI- 
GATION OF ROTATING STALL, BLADE VIBRATION, 
AND SURGE AT LOW AND INTERMEDIATE COM- 
PRESSOR SPEEDS. Merle C. Huppert, Eleanor L. 
Costilow, and Ray E. Budinger. May 1953. 47p. 
diagrs., photos., tabs. (NACA RM E53C19) 



DIFFUSION FACTOR FOR ESTIMATING LOSSES 
AND LIMITING BLADE LOADINGS IN AXIAL- 
FLOW-COMPRESSOR BLADE ELEMENTS. 
Seymour Lieblein, Francis C. Schwenk, and Robert 
L. Broderick. June 1953. 43p. diagrs., tabs. 
(NACA RM E53D011 



INVESTIGATION OF 16-INCH IMPULSE-TYPE 
SUPERSONIC COMPRESSOR WITH ROTOR TURN- 
ING PAST AXIAL DIRECTION. John J. Jacklitch, 
Jr., and Metvin J. Hartmann. July 1953. 29p. 
diners., photos. (NACA RM E53D13) 



INVESTIGATION OF AN AXIAL-FLOW- 
COMPRESSOR ROTOR WITH CIRCULAR- ARC 
BLADES OPERATmG UP TO A ROTOR-INLET 
RELATIVE MACH NUMBER OF 1.22. William H. 
Robbins and Frederick W. Glaser. July 1953. 63p. 
diagrs., photos., tabs. (NACA RM E53D24) 



INVESTIGATION OF A SUPERSONIC -COMPRESSOR 
ROTOR WITH TURNING TO AXIAL DIRECTION. I - 
ROTOR DESIGN AND PERFORMANCE. Edward R. 
Tysl, John F. Klapproth, and Melvin J. Hartmann. 
August 1953. 36p. diagrs., photos. 
(NACA RME53F23) 



UTOJZATION OF EXTERNAL -COMPRESSION DIF- 
FUSION PRINCIPLE IN DESIGN OF SHOCK -IN - 
ROTOR SUPERSONIC COMPRESSOR BLADING. 
John W. R. Creagh and John F. Klapproth. . 
September 1953. 37p. diagrs., photos., tab. 
(NACA RM E53F18) 



EXPERIMENTAL mVESTIGATION OF AN AXIAL- 
FLOW COMPRESSOR INLET STAGE OPERATING 
AT TRANSONIC RELATIVE INLET MACH NUM- 
BERS. HI - BLADE-ROW PERFORMANCE OF 
STAGE WITH TRANSONIC ROTOR AND SUBSONIC 
STATOR AT CORRECTED TIP SPEEDS OF 800 AND 
1000 FEET PER SECOND. Francis C. Schwenk, 
Seymour Lieblein, and George W. Lewis, Jr. 
September 1953. 69p. diagrs., photos., tabs. 
(NACA RM E53G17) 



INVESTIGATION OF AN AXIAL-FLOW COMPRES- 
SOR ROTOR HAVING NACA HIGH-SPEED BLADE 
SECTIONS (A 2 l8b SERIES) AT MEAN RADIUS 
RELATTVE INLET MACH NUMBERS UP TO 1.13. 
Melvyn Savage, John R. Erwin, and Robert P. 
Whitley. November 1953. 43p. diagrs., photos., 
tab. (NACA RM L53G02) 



INVESTIGATION OF A HIGH-PRESSURE -RATIO 
EIGHT -STAGE AXIAL-FLOW RESEARCH COMPRES- 
SOR WITH TWO TRANSONIC INLET STAGES. I - 
AERODYNAMIC DESIGN. Charles H. Voit. 
December 1953. 36p. diagrs., tabs. 
(NACA RM E53I24) 



INVESTIGATION OF A HIGH-PRESSURE-RATIO 
EIGHT-STAGE AXIAL-FLOW RESEARCH COMPRES- 
SOR WITH TWO TRANSONIC INLET STAGES. H - 
PRELIMINARY ANALYSIS OF OVER-ALL PERFORM- 
ANCE. Richard P. Geye, Ray E. Budinger, and 
Charles H. Voit. December 1953. 23p. diagrs., 
photos. (NACA RM E53J06) 



226 



(3) PROPULSION 



EXPERIMENTAL INVESTIGATION OF AN AXIAL- 
FLOW SUPERSONIC COMPRESSOR HAVING 
ROUNDED LEADING-EDGE BLADES WITH AN 
8-PERCENT MEAN THICKNESS-CHORD RATIO. 
Theodore J. Goldberg, Emanuel Boxer, and Peter T. 
Bernot. December 1953. 43p. diagrs., photos., 
tab. (NACA RM L53G16) 



ANALYSIS OF PERFORMANCE OF FOUR 
SYMMETRICAL-DIAGRAM-TYPE SUBSONIC 
INLET -STAGE AXIAL -FLOW COMPRESSORS. 
Robert J. Jackson. January 1954. 72p. diagrs., 
photos. (NACA RM E53K03) 



INVESTIGATION OF A 10-STAGE SUBSONIC AXIAL- 
FLOW RESEARCH COMPRESSOR. V - EFFECT OF 
REDUCING INLET-GUIDE -VANE TURNING ON 
OVER-ALL AND INLET-STAGE PERFORMANCE. 
Ray E. Budinger and George K. Serovy March 1954. 
37p. diagrs., phuto. (NACA RM E53H10) 



INVESTIGATION OF A SUPERSONIC -COMPRESSOR 
ROTOR WITH TURNING TO AXIAL DIRECTION. 
II - ROTOR COMPONENT OFF-DESIGN AND STAGE 
PERFORMANCE. Melvin J. Hartmann and Edward 
R, Tysl. March 1954. 31p. diagrs., photos. 
(NACA RM E53L24) 



REVIEW OF HIGH-PERFORMANCE AXIAL-FLOW- 
COMPRESSOR BLADE -ELEMENT THEORY. 
Seymour Liebleln. April 1954. 34p. diagrs. 
(NACARM E53L22) 



GENERAL CONSIDERATIONS OF MACH NUMBER 
EFFECTS ON COMPRESSOR-BLADE DESIGN. 
John F. Kiapproth. April 1954. 24p. diagrs., 
photos. (NACA RM E53L23a) 



EXPERIMENTAL INVESTIGATION OF ROTATING 
STALL AND BLADE VIBRATION IN THE AXIAL- 
FLOW COMPRESSOR OF A TURBOJET ENGINE. 
Merle C. Huppert, Howard F. Calvert, and Andre J. 
Meyer. April 1954. 24p. diagrs., tabs. 
(NACA RM E54A08) 



APPLICATION OF RADIAL-EQUILIBRIUM CONDI- 
TION TO AXIAL-FLOW TURBOMACHTNE DESIGN 
INCLUDING CONSIDERATION OF CHANGE OF . 
ENTROPY WITH RADIUS DOWNSTREAM OF BLADE 
ROW. James E. Hatch, Charles C. Giamati, and 
Robert J. Jackson. April 1954. 52p. diagrs. 
(NACA RM E54A20) 



INVESTIGATION OF IMPULSE -TYPE SUPERSONIC 
COMPRESSOR WITH HUB-TIP RATIO OF 6 AND 
TURNING TO AXIAL DIRECTION. I - PERFORM- 
ANCE OF ROTOR ALONE Ward W. Wilcox. May 
1954. 41p diagrs., photos., tab. 
(NACA RM E54B25) 



PERFORMANCE OF A SUPERSONIC ROTOR HAVING 
HIGH MASS FLOW. Ralph L, Schacht, Arthur W. 
Goldstein, and Harvey E. Neumann. July 1954. 
34p. diagrs., photo., tab. (NACA RM E54D22) 



INVESTIGATION OF A 10-STAGE SUBSONIC AXIAL - 
FLOW RESEARCH COMPRESSOR. VI - PERFORM- 
ANCE EVALUATION AND FLOW DISTRIBUTIONS IN 
THE FIRST, FIFTH, AND TENTH STAGES. Ray E. 
Budinger. August 1954. 42p. diagrs., photo., tabs. 
(NACA RM E54F28) 



INVESTIGATION OF SUPERSONIC-COMPRESSOR 
ROTORS DESIGNED WITH EXTERNAL COMPRES- 
SION. Lawrence J. Jahnsen and Melvin J. ■- 
Hartmann. September 1954. 41p. diagrs., photos. 
(NACA RM E54G27a) 



INVESTIGATION OF THREE HIGHLY LOADED 
SUBSONIC-INLET-STAGE AXIAL-FLOW COMPRES- 
SORS EMPLOYING VARYING RADIAL GRADIENTS 
OF ENERGY ADDITION. Raymond M. Standahar. 
October 1954. 33p. diagrs., photos., tabs. 
(NACA RM E54G20) 



INVESTIGATION OF A HIGH-PRESSURE-RATIO 
EIGHT-STAGE AXIAL-FLOW RESEARCH COMPRES- 
SOR WITH TWO TRANSONIC INLET STAGES. HI - 
INDr/IDUAL STAGE PERFORMANCE CHARACTER- 
ISTICS. Charles H. Voit and Richard P. Geye. 
November 1954. 25p. diagrs., photo. 
(NACA RM E54H17) 



EXPERIMENTAL INVESTIGATION OF CONTROL 
SIGNALS AND THE NATURE OF STALL AND SURGE 
BEHAVIOR IN A TURBOJET ENGINE. G. J. Delio 
and P. M. Stiglic. December 1954. 62p. diagrs. 
(NACA RM E54I15) 



PRELIMINARY INVESTIGATION OF THE STRENGTH 
AND ENDURANCE OF PLASTIC-IMPREGNATED 
FIBERGLASS COMPRESSOR BLADES. Donald F. 
Johnson and Andre J. Meyer, Jr. January 1955. 
21p. diagrs., photos. (NACA RM E54I27a) 



EXPERIMENTAL INVESTIGATION OF AN AXIAL- 
FLOW SUPERSONIC COMPRESSOR HAVING SHARP 
LEADING-EDGE BLADES WITH AN 8-PERCENT 
MEAN THICKNESS-CHORD RATIO AND OF THE 
EFFECT OF A LEADING-EDGE RADIUS. Theodore 
J. Goldberg. February 1955. 33p. diagrs., photo. 
(NACA RM L54K16) 



DESIGN AND PERFORMANCE OF A 1400-FOOT-PER- 
SECOND-TIP-SPEED SUPERSONIC COMPRESSOR 
ROTOR. John F. Kiapproth, John J. Jacklitch, Jr., 
and Edward R. Tysl. April 1955. 48p. diagrs., 
photo., tab. (NACA RM E55A27) 



ANALYSIS OF AERODYNAMIC BLADE-LOADING- 
LIMIT PARAMETERS FOR NACA 65-(Cj o A 10 )10 

COMPRESSOR-BLADE SECTIONS AT LOW SPEEDS. 
Melvyn Savage . April 1955. 32p. diagrs. 
(NACA RM L54L02a) 



INVESTIGATION OF A HIGH-PRESSURE-RATIO 
EIGHT -STAGE AXIAL-FLOW RESEARCH COM- 
PRESSOR WITH TWO TRANSONIC INLET STAGES. 
V - PRELIMINARY ANALYSIS OF OVER-ALL PER- 
FORMANCE OF MODIFIED COMPRESSOR. 
Raymond M. Standahar and Richard P. Geye. May 
1955. 20p. diagrs., photos. (NACA RM E55A03) 



STEADY-STATE AND SURGE CHARACTERISTICS 
OF A COMPRESSOR EQUIPPED WITH VARIABLE 
INLET GUIDE VANES OPERATING IN A TURBOJET 

ENGINE. Lewis E. Wallner and Robert J. Lubick. 
June 1955. 54p. diagrs., photos. (NACA RM E54I28) 



COMPRESSOR-BLADE VIBRATION AND PERFORM- 
ANCE IN A J47-23 TURBOJET ENGINE UNDER 
CONDITIONS OF ROTATING STALL. Morgan P. 
Hanson, Donald F. Johnson, and Andre J. Meyer, Jr. 
June 1955. 18p. diagrs., tab. (NACA RM E54L20a) 



INVESTIGATION OF A HIGH-PRESSURE-RATIO 

EIGHT -STAGE AXIAL-FLOW RESEARCH COM- 
PRESSOR WITH TWO TRANSONIC INLET STAGES. 
IV - MODIFICATION OF AERODYNAMIC DESIGN 
AND PREDICTION OF PERFORMANCE. Richard P. 
Geye and Charles H. Voit. June 1955. 22p. diagrs., 
tab. (NACA RM E55B28) 



(3) PROPULSION 



227 



INVESTIGATION OF IMPULSE-TYPE SUPERSONIC 
COMPRESSOR WITH HUB-TIP RATIO OF 0.6 AND 
TURNING TO AXIAL DIRECTION. II - STAGE PER- 
FORMANCE WITH THREE DIFFERENT SETS OF 
STATORS. WardW. Wilcox. August 1355. 49p. 
diagrs., photos., tab. (NACA RM E55F28) 



EFFECTS OF INLET-AIR-FLOW DISTORTION ON 
STEADY-STATE ALTITUDE PERFORMANCE OF AN 
AXIAL- FLOW TURBOJET ENGINE . William 
Conrad, Morgan P. Hanson, and John E. McAulay. 
September 1955. 47p. diagrs., photo 
(NACA RM E55A04) 



HIGH-SPEED CASCADE TESTS OF A BLADE SEC- 
TION DESIGNED FOR TYPICAL HUB CONDITIONS 
OF HIGH-FLOW TRANSONIC ROTORS Melvyn 
Savage, A. Richard Felix, and James C. Emery. 
September 1955. 48p. diagrs., photos., tab. 
(NACA RM L55F07) 



THROAT-AREA DETERMINATION FOR A CASCADE 
OF DOUBLE -CIRCULAR -ARC BLADES. Linwood 
C. Wright and Richard Schwind. November 1955. 
20p. diagrs. (NACA RM E55H25a) 



INVESTIGATION OF A HIGH-PRESSURE-RATIO 
EIGHT -STAGE AXIAL-FLOW RESEARCH COM- 
PRESSOR WITH TWO TRANSONIC INLET STAGES. 
VI - OVER-ALL PERFORMANCE, ROTATING 
STALL, AND BLADE VIBRATION AT LOW AND 
INTER MFniATE COMPRESSOR SPEEDS. Raymond 
M. Standahar, Morgan P. Hanson, and Richard P. 
Geve. November 1955. 21p. diagrs. 
(NACA RM E55I13) 



USE OF SHADOWGRAPH TECHNIQUE IN THE 
ANALYSIS OF THE PERFORMANCE OF TWO 
SUPERSONIC AXIAL-FLOW COMPRESSOR ROTORS 
OPERATING OVER A MEAN RADIUS RELATIVE 
INLET MACH NUMBER RANGE OF 0,85 TO 1.7. 
Theodore J. Goldberg and James R. Sterrett. 
April 1956. 48p. diagrs., photos. 
(NACARM L56A05) 



AERODYNAMIC DESIGN OF AXIAL -FLOW COM- 
PRESSORS. VOLUME I. Compressor and Turbine 
Research Division. Edited by Irving A. Johnsen and 
Robert O. Bullock. August 1956. xii, 406p. diagrs., 
photos., tab. (NACA RM E56B03) 



AERODYNAMIC DESIGN OF AXIAL-FLOW COM- 
PRESSORS. VOLUME II. Compressor and Turbine 
Research Division. Edited by Irving A. Johnsen and 
Robert O. Bullock. August 1956. x, 275p. diagrs., 
tabs. (NACA RM E56B03a) 



AERODYNAMIC DESIGN OF AXIAL-FLOW COM- 
PRESSORS. VOLUME III. Compressor and Turbine 
Research Division. Edited by Irving A. Johnsen and 
Robert O. Bullock. August 1956. xii, 364p. diagrs., 
photos., tabs. (NACA RM E56B03b) 



EFFECT OF DESIGN OVER-ALL COMPRESSOR 
PRESSURE RATIO DIVISION ON ACCELERATION 
CHARACTERISTICS OF THREE HYPOTHETICAL 
TWO-SPOOL TURBOJET ENGINES. Richard E. 
Filippi and James F. Dugan, Jr. August 1956. 26p. 
diagrs. (NACA RM E56D13) 



ANALYSIS OF TURBOMACHINE VISCOUS LOSSES 
AFFECTED BY CHANGES IN BLADE GEOMETRY. 
James W. Miser, Warner L. Stewart, and Warren J. 
Whitney. October 1956. 50p. diagrs., tab. 
(NACA RM E56F21) 



ANALYSIS OF EXPERIMENTAL LOW-SPEED LOSS 
AND STALL CHARACTERISTICS OF TWO- 
DIMENSIONAL COMPRESSOR BLADE CASCADES. 

Seymour Lieblein. March 1957. 64p. diagrs., 
tabs. (NACA RM E57A28) 



INVESTIGATION OF THE EFFECT OF VELOCITY 
DIAGRAM ON INLET TOTAL-PRESSURE DISTOR- 
TIONS THROUGH SINGLE-STAGE SUBSONIC AXIAL- 
FLOW COMPRESSORS. George C. Ashby, Jr. 
April 1957. 21p. diagrs., photo. 
(NACA RM L57A03) 



LOW-SPEED CASCADE INVESTIGATION OF THIN 
LOW-CAMBER NACA 65-SERIES BLADE SECTIONS 
AT HIGH INLET ANGLES. James C. Emery. June 
1957. 93p. diagrs., tab. (NACARM L57E03) 



EFFECT OF SWEEP ON PERFORMANCE OF COM- 
PRESSOR BLADE SECTIONS AS INDICATED BY 
SWEPT-BLADE ROTOR, UNSWEPT-BLADE 
ROTOR, AND CASCADE TESTS. WUUam R. 
Godwin. July 1957. 43p. diagrs. (NACA TN 4062) 



DETERMINATION OF SURGE AND STALL LIMITS 
OF AN AXIAL- FLOW TURBOJET ENGINE FOR 
CONTROL APPLICATIONS. Ross D. Schmidt, 
George Vasu, and Edward W. McGraw. September 
1957. 29p. diagrs., tab. (NACA TN 3585. 
Supersedes RM E53B10) 



NACA 65-SERIES COMPRESSOR ROTOR PERFORM- 
ANCE WITH VARYING ANNULUS-AREA RATIO, 
SOLIDITY, BLADE ANGLE, AND REYNOLDS NUM- 
BER AND COMPARISON WITH CASCADE RESULTS. 
Wallace M. Schulze, John R. Erwin, and George C. 
Ashby, Jr. October 1957. 62p. diagrs., photos., 
tab. (NACA TN 4130. Supersedes RM L52L17) 



COMPARISON OF PERFORMANCE OF TWO AERO- 
DYNAMICALLY SIMILAR 14-INCH-DIAMETER 
SINGLE-STAGE COMPRESSOR ROTORS OF DIFFER- 
ENT CHORD LENGTH. Marvin I. Kussoy and 
Daniel Bachkin. February 1958. 39p. diagrs., 
photos., tabs, (NACA RM E57I03) 



STALL PROPAGATION IN A CASCADE OF AIR- 
FOILS. Anthony R. Kriebel, Barry S. Seidel, and 
Richard G. Schwind, Massachusetts Institute of 
Technology. June 1958. 122p. diagrs., photos., 
tabs. (NACA TN 4134) 



EXPERIMENTAL INVESTIGATION OF AN IMPULSE- 
TYPE SUPERSONIC COMPRESSOR ROTOR HAVING 
A TURNING OF 73<> AT THE MEAN RADIUS. James 
R. Sterrett. June 1958. 35p. diagrs., photos., tabs. 
(NACA TN 4252) 



DESIGN AND TESTS OF A SIX-STAGE AXIAL -FLOW 
COMPRESSOR HAVING A TIP SPEED OF 550 FEET 
PER SECOND AND A FLAT OPERATING CHARAC- 
TERISTIC AT CONSTANT SPEED. Willard R. 
Westphal and John W. Maynard, Jr. June 1958. 
57p. diagrs., photos., tabs. (NACA TN 4253)T 



ANALYTICAL RELATION FOR WAKE MOMENTUM 
THICKNESS AND DIFFUSION RATIO FOR LOW- 
SPEED COMPRESSOR CASCADE BLADES. Seymour 
Lieblein. August 1958. 31p. diagrs. 
(NACA TN4318) 



228 



(3) PROPULSION 



PERFORMANCE AT LOW SPEEDS OF COMPRESSOR 
ROTORS HAVING LOW-CAMBERED NACA 65- 
SERIES BLADES WITH HIGH INLET ANGLES AND 
LOW SOLIDITIES. James C. Emery and Paul W. 
Howard. August 1958. 28p. diagrs. 
(NACA TN 4344) 



APPROXIMATE SOLUTIONS OF A CLASS OF SIMI- 
LARITY EQUATIONS FOR THREE-DIMENSIONAL, 
LAMINAR, INCOMPRESSIBLE BOUNDARY -LAYER 
FLOWS. Arthur G. Hansen and Howard Z. Herzig. 
September 1958. 26p. diagrs. (NACA TN 4375> 



(3.6.1.2) 
RADIAL, FLOW 



ANALYTICAL AND EXPERIMENTAL INVESTIGA- 
TION OF THRUST AUGMENTATION OF AXIAL- 
AND CENTRIFUGAL-COMPRESSOR TURBOJET 
ENGINES BY INJECTION OF WATER AND ALCO- 
HOL IN COMBUSTION CHAMBERS. David S. 
Gabriel, Harry W.Dowman, and William L. Jones. 
April 13, 1950. 43p. diagrs., photo. 
(NACA RM E9K29) 



DESIGN AND TEST OF MIXED-FLOW IMPELLERS. 
VIII - COMPARISON OF EXPERIMENTAL RESULTS 
FOR THREE IMPELLERS WITH SHROUD REDE- 
SIGNED BY RAPID APPROXIMATE METHOD. 
Walter M. Osborn, Kenneth J. Smith, and Joseph T. 
Hamrick. February 1957. 32p. diagrs., photos. 
(NACA RM E56L07) 



(3.6.1.3) 
MIXED FLOW 



DESIGN AND PERFORMANCE OF AN EXPERIMEN- 
TAL AXIAL -DISCHARGE MDCED-FLOW COM- 
PRESSOR. Ill - OVER-ALL PERFORMANCE OF 
IMPELLER AND SUPERSONIC-DIFFUSER COMBI- 
NATION. Ward W. Wilcox and William H. Robbins. 
April 30, 1951. 26p. diagrs., photo. 
(NACA RM E51A02) 



PERFORMANCE OF A SWEPT LEADING EDGE 
ROTOR OF THE SUPERSONIC TYPE WITH MDCED 
FLOW. Arthur W. Goldstein and Ralph L. Schacht. 
January 1953. 34p . diagrs., photo., tab. 
(NACA RM E52K03) 



DESIGN AND TEST OF MDCED-FLOW IMPELLERS. 
in - DESIGN AND EXPERIMENTAL RESULTS FOR 
IMPELLER MODEL MFI-2A AND COMPARISON 
WITH IMPELLER MODEL MFI-'IA. Joseph T. 
Hamrick, Walter M. Osborn, and William L. Beede. 
March 1953. 34p. diagrs., photo., tab. 
(NACA RM E52L22a) 



PERFORMANCE OF A SUPERSONIC MIXED-FLOW 
ROTOR WITH A SWEPT LEADING EDGE AND 0.52 
INLET RADIUS RATIO. Arthur W. Goldstein and 
Ralph L. Schacht. November 1953 34p. diagrs., 
photos., tab. (NACA RM ET)3H27) 



DESIGN AND TEST OF MIXED-FLOW IMPELLERS. 
IV - EXPERIMENTAL RESULTS FOR IMPELLER 
MODELS MFI-1 AND MFI-2 WITH CHANGES IN 
BLADE HEIGHT. Joseph T. Hamrick, William L. 
Beede, and Joseph R. Withee, Jr. February 1954. 
32p. diagrs., photos. (NACA RM E53L02) 



PERFORMANCE OF MLXED-FLOW IMPELLER, 
MODEL MFI-1B, WITH DIFFUSER VANES AT 
EQUIVALENT IMPELLER SPEEDS FROM 1100 TO 
1700 FEET PER SECOND. Walter M. Osborn. 
June 1954. 16p. diagrs., photo. 
(NACA RM E54D23) 



PERFORMANCE OF A SUPERSONIC ROTOR HAVING 
HIGH MASS FLOW. Ralph L. Schacht, Arthur W. 
Goldstein, and Harvey E. Neumann. July 1954. 
34p. diagrs., photo., tab. (NACA RM E54D22) 



PERFORMANCE OF A SUPERSONIC COMPRESSOR 
WITH SWEPT AND TILTED DIFFUSER BLADES. 
Arthur W. Goldstein and Ralph L. Schacht. March 
1955. 32p. diagrs., photo. (NACA RM E54L29) 



DESIGN AND TEST OF MDCED-FLOW IMPELLERS. 
V - DESIGN PROCEDURE AND PERFORMANCE 
RESULTS FOR TWO VANED DIFFUSERS TESTED 
WITH IMPELLER MODEL MFI-1B- Joseph T. 
Hamrick and Walter M. Osborn. July 1955. 32p. 
diagrs., photos. (NACA RM E55E13) 



DESIGN AND TEST OF MIXED-FLOW IMPELLERS. 
VI - PERFORMANCE OF PARABOLIC -BLADED 
IMPELLER WITH SHROUD REDESIGNED BY RAPID 
APPROXIMATE METHOD. Kenneth J. Smith and 
Walter M. Osborn. September 1955. 22p. diagrs., 
photo., tab. (NACA RM E55F23) 



DESIGN AND TEST OF MLXED-FLOW IMPELLERS. 
Vn - EXPERIMENTAL RESULTS FOR PARABOLIC - 
BLADED IMPELLER WITH ALTERNATE BLADES 
CUT BACK TO FORM SPLITTER VANES. Walter M. 
Osborn. March 1956. 13p. diagrs., photo. 
(NACARM E55L15) 



(3.6.2) 
STRESS AND VIBRATION 



INVESTIGATION OF A 10-STAGE SUBSONIC AXIAL- 
FLOW RESEARCH COMPRESSOR, in - INVESTI- 
GATION OF ROTATING STALL, BLADE VIBRATION, 
AND SURGE AT LOW AND INTERMEDIATE COM- 
PRESSOR SPEEDS. Merle C. Huppert, Eleanor L. 
Costilov, and Ray E. Budinger. May 1953. 47p. 
diagrs., photos., tabs. (NACA RM E53C19) 



EXPERIMENTAL mVESTIGATlON OF ROTATING 
STALL AND BLADE VIBRATION IN THE AXIAL- 
FLOW COMPRESSOR OF A TURBOJET ENGINE. 
Merle C. Huppert, Howard F. Calvert, and Andre J. 
Meyer. April 1954. 24p. diagrs., tabs. 
(NACA RM E54A08) 



EXPERIMENTAL INVESTIGATION OF CONTROL 
SIGNALS AND THE NATURE OF STALL AND SURGE 
BEHAVIOR IN A TURBOJET ENGINE. G. J. Delio 
and P. M. Stiplic. December 1954. 62p. diagrs. 
(NACA RM E54I15) 

PRELIMINARY INVESTIGATION OF THE STRENGTH 
AND ENDURANCE OF PLASTIC-IMPREGNATED 
FIBERGLASS COMPRESSOR BLADES. Donald F. 
Johnson and Andre J. Meyer, Jr. January 1955. 
21p. diagrs., photos. (NACA RM E54I27a) 



COMPRESSOR -BLADE VIBRATION AND PERFORM- 
ANCE IN A J47-23 TURBOJET ENGINE UNDER 
CONDITIONS OF ROTATING STALL. Morgan P. 
Hanson, Donald F. Johnson, and Andre J. Meyer, Jr. 
June 1955. 18p. diagrs., tab. (NACA RM E54L20a) 



(3) PROPULSION 



.229 



INVESTIGATION OF A HIGH -PRESSURE -RATIO 
EIGHT -STAGE AXIAL-FLOW RESEARCH COM- 
PRESSOR WITH TWO TRANSONIC INLET STAGES. 
VI - OVER-ALL PERFORMANCE, ROTATING 
STALL, AND BLADE VIBRATION AT LOW AND 
INTERMEDIATE COMPRESSOR SPEEDS. Raymond 
M. Standahar, Morgan P. Hanson, and Richard P. 
Gove. November 1955. 21 u. diagrs. 
(NACA RM E55I13) 



FACTORS THAT AFFECT OPERATIONAL RELI- 
ABILITY OF TURBOJET ENGINES. Lewis 
Laboratory Staff. January 1956. 376p. diagrs., 
photos., tabs. (NACA RM E55H02) 



AERODYNAMIC DESIGN OF AXIAL-FLOW COM- 
PRESSORS. VOLUME III. Compressor antVTurbine 
Research Division. Edited by Irving A. Johnsen and 
Robert O. Bullock. August 1956. xii, 364p. chagrs., 

photos., tabs. (NACA RM E56B03b) 



INVESTIGATION OF SOME MECHANICAL PROP- 
ERTIES OF THERMENOL COMPRESSOR BLADES. 
Donald F. Johnson. October 1957. 14p. diagrs., 
photo. (NACA TN 4097) 



(3.6.3) 
MATCHING 



TURBOPROP -ENGINE DESIGN CONSIDERATIONS. 
I - ETFECT OF MODE OF ENGINE OPERATION ON 
PERFORMANCE OF TURBOPROP ENGINE WITH 
CURRENT COMPRESSOR PRESSURE RATIO.. 
Elmer H. Davison. May 1955. 34p. diagrs. 
(NACA RM E54D19) 



TURBOPROP-ENGINE DESIGN CONSIDERATIONS. 
II - DESIGN REQUIREMENTS AND PERFORMANCE 
OF TURBOPROP ENGINES WITH A SINGLE -SPOOL 
HIGH-PRESSURE-RATIO COMPRESSOR. Elmer H. 
Davison and Margaret C. Staiia. May 1955. 32p. 
diagrs., tabs. (NACA RM E55B18) 



INVESTIGATION OF A HIGH-PRLSSURE-RATIO 
EIGHT -STAGE AXIAL-FLOW RESEARCH COM- 
PRESSOR WITH TWO TRANSONIC INLET STAGES. 
TV - MODIFICATION OF AERODYNAMIC DESIGN 
AND PREDICTION OF PERFORMANCE. Richard P. 
Geye and Charles H. Voit. June 1955. 22p. diagrs., 
tab. (NACA RM E55B28) 



PERFORMANCE OF A HIGH -SOLIDITY HIGH- 
PRESSURE -RATIO TRANSONIC ROTOR. Harvey E. 
Neumann. November 1955. 29p. diagrs., photo. 

(NACA RM E55I19) 



AERODYNAMIC DESIGN OF AXIAL -FLOW COM- 
PRESSORS. VOLUME II. Compressor and Turbine 
Research Division. Edited by Irving A. Johnsen and 
Robert O. Bullock. August 1956. x, 275p. diagrs., 
tabs. (NACA RM E56B03a) 



AERODYNAMIC DESIGN OF AXIAL-FLOW COM- 
PRESSORS. VOLUME III. Compressor and Turbine 
Research Division. Edited by Irving A. Johnsen and 
Robert O. Bullock. August 1956. xii, 364p. diagrs,, 
photos., tabs. (NACA RM E56B03b) 



EFFECT OF DESIGN OVER-ALL COMPRESSOR 
PRESSURE RATIO DIVISION ON ACCELERATION 
CHARACTERISTICS OF THREE HYPOTHETICAL 
TWO-SPOOL TURBOJET ENGINES. Richard E. 
Filippi and James F. Dugan, Jr. August 1956. 26p. 
diagrs. (NACA RM E56D13) 



230 



(3) PROPULSION 



(3.7) 
Turbines 



MECHANICAL DESIGN ANALYSIS OF SEVERAL 
NONCRITICAL AIR-COOLED TURBINE DISKS AND 
A CORRUGATED-INSERT AIR-COOLED TURBINE 
ROTOR BLADE. MerlandL. Mpseson, Morton H. 
Krasner, and Robert R. Ziemer. July 1953. 49p. 
diagrs., photos., tabs. (NACA RM E53E21) 



DESIGN AND EXPERLMENTAL INVESTIGATION OF 
LIGHTWEIGHT BASES FOR AIR-COOLED TURBINE 
ROTOR BLADES. John C. Freche and Roy A. 
McKinnon. July 1954. 27p. diagrs., photos., tab. 
(NACA RM E54E10) 



EFFECTIVENESS OF A TURBOJET TUBULAR. 
COMBUSTOR IN SCREENING THE TURBINE FROM 
FOREIGN OBJECTS. Patrick T. Chiarito. July 
1955. 20p. diagrs., photos. (NACA RM E55E16) 



(3.7.1) 

FLOW THEORY AND 

EXPERIMENT 



A TWO-DIMENSIONAL CASCADE STUDY OF THE 
AERODYNAMIC CHARACTERISTICS OF A 
TURBINE-ROTOR BLADE SUITABLE FOR AIR 
COOLING. Henry W. Plohr and Cavour H. Hauser. 
September 1951. 15p. diagrs., photos. 
(NACA RM E51G18) 



AN EXPERIMENTAL CASCADE STUDY OF THE 
EFFECTS OF A SOLIDITY REDUCTION ON THE 
TWO-DIMENSIONAL AERODYNAMIC CHARACTER- 
ISTICS OF A TURBINE-ROTOR BLADE SUITABLE 
FOR AIR COOLING. Henry W. Plohr and William J. 
Nusbaum. May 1952. 17p. diagrs., photos.. 
(NACA RM E52B27) 



APPLICATION OF RADIAL-EQUILIBRIUM CONDI- 
TION TO AXIAL -FLOW TURBOMACHTNE DESIGN 
INCLUDING CONSIDERATION OF CHANGE OF 
ENTROPY WITH RADIUS DOWNSTREAM OF BLADE 
ROW. James E. Hatch, Charles C. Giamati, and 
Robert J. Jackson. April 1954. 52p. diagrs. 
(NACA RM E54A20) 



EFFECT OF NOZZLE SECONDARY FLOWS ON 
TURBINE PERFORMANCE AS INDICATED BY EXIT 
SURVEYS OF A ROTOR. Warren J. Whitney, 
Howard A. Buckner, Jr., and Daniel E. Monroe. 
April 1954. lip. diagrs. (NACA RM E54B03) 



INVESTIGATION OF COMPRESSIBLE FLOW 
MDCING LOSSES OBTAINED DOWNSTREAM OF A 
BLADE ROW. Warner L. Stewart. December 1954. 
21p. diagrs. (NACA RM E54I20) 



QUALITATIVE STUDY OF FLOW CHARACTERIS- 
TICS THROUGH SINGLE-STAGE TURBINES AS 
MADE FROM ROTOR-EXIT SURVEYS. Robert Y. 
Wong, James W. Miser, and Warner L. Stewart. 
March 1956. 26p. diagrs. (NACA RM E55K21) 



(3.7.1.1) 
AXIAL FLOW 



COMPARISON OF MEASURED EFFICIENCIES OF 
NINE TURBINE DESIGNS WITH EFFICIENCIES PRE- 
DICTED BY TWO EMPIRICAL METHODS. Robert E. 
English and Richard H. Cavicchi. August 1951. 23p. 
diagrs., tab. (NACA RM E51F13) 



A TWO-DIMENSIONAL CASCADE STUDY OF THE 
AERODYNAMIC CHARACTERISTICS OF A 
TURBINE-ROTOR BLADE SUITABLE FOR AIR 
COOLING. Henry W. Plohr and Cavour H. Hauser. 
September 1951. 15p. diagrs., photos. 
(NACA RM E51G18) 



COLD-AIR INVESTIGATION OF A TURBINE WITH 
NON TWISTED ROTOR BLADES SUITABLE FOR AIR 
COOLING. Thomas R. Heaton, William R. Slivka, 
and Leonard F. Westra. March 1952. 34p. diagrs., 
photos. (NACA RM E52A25) 



AN EXPERIMENTAL CASCADE STUDY OF THE 
EFFECTS OF A SOLIDITY REDUCTION ON THE 
TWO-DIMENSIONAL AERODYNAMIC CHARACTER- 
ISTICS OF A TURBINE-ROTOR BLADE SUITABLE 
FOR AIR COOLING. Henry W. Plohr and William J. 
Nusbaum. May 1952. 17p. diagrs., photos. 
(NACA RM E52B27) 



COMPONENT AND OVER -ALL PERFORMANCE 
EVALUATION OF AN AXIAL-FLOW TURBOJET 
ENGINE OVER A RANGE OF ENGINE -INLET 
REYNOLDS NUMBERS. Curtis L. Walker. S- C. 
Huntley, andW. M. Braithwaite. July 1952. 42p. 
diagrs., tabs. (NACA RM E52B08) 



TURBINE DESIGN CONSIDERATIONS FOR 
TURBINE -PROPELLER ENGINE OPERATING OVER 
A RANGE OF FLIGHT CONDITIONS. Elmer H. 
Davison. June 1953. 20p. diagrs., tab. 
(NACA RM E53D16) 



DESIGN AND EXPERIMENTAL INVESTIGATION OF 
TRANSONIC TURBINE WITH SLIGHT NEGATIVE 
REACTION ACROSS ROTOR HUB. Warner L. 
Stewart, Robert Y. Wong, and David G. Evans. 
March 1954. 40p. diagrs., photo., tabs. 
(NACARM E53L29a) 



LOW-VELOCITY TURNING AS A MEANS OF MINI- 
MIZING BOUNDARY -LAYER ACCUMULATIONS 
RESULTING FROM SECONDARY FLOWS WITHIN 
TURBINE STATORS. Warner L. Stewart and Robert 
Y. Wong. May 1954. 18p. diagrs., photo. 
(NACARM E54B16) 



INVESTIGATION OF EFFECT OF INCREASED DIF- 
FUSION OF ROTOR-BLADE SUCTION -SURFACE 
VELOCITY ON PERFORMANCE OF TRANSONIC 
TURBINE. Robert Y. Wong, Daniel E. Monroe, and 
William T. Wintucky. August 1954. 19p. diagrs., 
photo., tab. (NACA RM E54F03) 



(3) PROPULSION 



231 



INVESTIGATION OF TRANSONIC TURBINE DE- 
SIGNED FOR ZERO DIFFUSION OF SUCTION- 
SURFACE VELOCITY. Warren J. Whitney, Daniel 
E. Monroe, and Robert Y. Wong- August 1954. 
20p. diagrs., photo., tab. (NACA RM E54F23) 



INVESTIGATION OF A TRANSONIC TURBINE DE- 
SIGNED FOR A MAXIMUM ROTOR-BLADE SUCTION- 
SURFACE RELATIVE MACH NUMBER OF 1.57. 
Warren J. Whitney, Robert Y. Wong, and Daniel E. 
Monroe. October 1954. 22p. diagrs., photo., tabs. 
(NACA RM E54G27) 



CORRELATION OF TURBINE-BLADE -ELEMENT 
LOSSES BASED ON WAKE MOMENTUM THICKNESS 
WITH DIFFUSION PARAMETER FOR A SERIES OF 
SUBSONIC TURBINE BLADES IN TWO- 
DIMENSIONAL CASCADE AND FOR FOUR TRAN- 
SONIC TURBINE ROTORS. Robert Y. Wong and 
Warner L. Stewart. April 1955. 31p. diagrs. 
(NACARME55B08) 



PRELIMINARY INVESTIGATION OF HOLLOW- 
BLADED TURBINES HAVING CLOSED AND OPEN 
BLADE TIPS. Gordon T. Smith and Robert O. 
Hickel. August 1955. 18p. diagrs., photo., tab. 

(NACARM E55F27a) 



EFFECT OF HIGH ROTOR PRESSURE -SURFACE 
DIFFUSION ON PERFORMANCE OF A TRANSONIC 
TURBINE. James W. Miser, Warner L. Stewart, 
and Daniel E. Monroe. November 1955. 35p. 
diagrs., photos., tabs. {NACA RM E55H29a) 



USE OF EFFECTIVE MOMENTUM THICKNESS IN 
DESCRIBING TURBINE ROTOR-BLADE LOSSES. 
Warner L. Stewart, Warren J. Whitney, and James 
W. Miser. May 1956. 26p. diagrs. 
(NACA RM E56B29) 



VISUALIZATION OF ROTOR TIP SECONDARY 
FLOWS WITH BLADE TIP AIR DISCHARGE AND 
SUCTION IN A LOW -SPEED TURBINE . Milton G . 
Kofskey and Hubert W. Allen. August 1956. 28p. 
diagrs., photos. (NACARM E56E16) 



ANALYSIS OF TURBOMACHINE VISCOUS LOSSES 
AFFECTED BY CHANGES IN BLADE GEOMETRY. 

James W. Miser, Warner L. Stewart, and Warren J. 
Whitney. October 1956. 50p. diagrs., tab. 
(NACA RM E56F21) 



ANALYTICAL INVESTIGATION OF SINGLE -STAGE - 
TURBINE EFFICIENCY CHARACTERISTICS IN 
TERMS OF WORK AND SPEED REQUIREMENTS. 
Warner L. Stewart. October 1956. 45p. diagrs. 
(NACA RM E56G31) 



ANALYSIS OF EFFICIENCY CHARACTERISTICS OF 
A SINGLE-STAGE TURBINE WITH DOWNSTREAM 
STATORS IN TERMS OF WORK AND SPEED RE- 
QUIREMENTS, William T. Wintucky and Warner L. 

Stewart. January 19^7 28p. diagrs. 
(NACA RM E56J19) 



ANALYSIS OF TWO-STAGE-TURBINE EFFICIENCY 
CHARACTERISTICS IN TERMS OF WORK AND 
SPEED REQUIREMENTS. Warner L. Stewart and 
William T. Wintucky. August 1957. 45p. diagrs., 
tabs. (NACA RM E57F12) 



ANALYTICAL INVESTIGATION OF MULTISTAGE - 
TURBINE EFFICIENCY CHARACTERISTICS IN 
TERMS OF WORK AND SPEED REQUIREMENTS. 
Warner L. Stewart. February 1958. 18p. diagrs. 
(NACA RM E57K22b) 



ANALYSIS OF TWO-STAGE COUNT ERROTATING 
TURBINE EFFICIENCIES IN TERMS OF WORK AND 
SPEED REQUIREMENTS. William T. Wintucky and 
Warner L. Stewart. March 1958. 33p. diagrs., 
tabs. (NACA RM E57L05) 



MAXIMUM THEORETICAL TANGENTIAL VELOCITY 
COMPONENT POSSIBLE FROM STRAIGHT-BACK 
CONVERGING AND CONVERGING-DIVERGING 
STATORS AT SUPERCRITICAL PRESSURE RATIOS. 
Thomas P. Moffitt. April 1958. 21p. diagrs. 
(NACA TN 4271) 



TORQUE-SPEED CHARACTERISTICS FOR HIGH- 
SPECIFIC -WORK TURBINES. Warner L. Stewart. 
September 1958. 21p. diagrs. (NACA TN 4379) 



(3.7.1.3) 
MIXED FLOW 



INVESTIGATION OF TURBINES FOR DRIVING 
SUPERSONIC COMPRESSORS. I - DESIGN AND 
PERFORMANCE OF FIRST CONFIGURATION. 
Warner L. Stewart, Harold J. Schum, and Warren J. 
Whitney. June 1952. 27p. diagrs., photo. 
{NACA RM E52C25) 



INVESTIGATION OF TURBINES FOR DRIVING 
SUPERSONIC COMPRESSORS. II - PERFORMANCE 
OF FIRST CONFIGURATION WITH 2.2-PERCENT 
REDUCTION IN NOZZLE FLOW AREA. Warner L. 
Stewart, Harold J. Schum, and Robert Y. Wong. 
July 1952. 14p. diagrs., tab. (NACA RM E52E26) 



INVESTIGATION OF TURBINES FOR DRIVING 
SUPERSONIC COMPRESSORS. Ill - FIRST CON- 
FIGURATION WITH FOUR NOZZLE SETTINGS AND 
ONE NOZZLE MODIFICATION. Warner L. Stewart, 
Warren J. Whitney, and Daniel E. Monroe. March 
1953. 28p. diagrs., photo., tab. 
(NACARM E53A20) 



INVESTIGATION OF TURBINES FOR DRIVING 
SUPERSONIC COMPRESSORS. TV - DESIGN AND 
PERFORMANCE OF SECOND CONFIGURATION 
INCLUDING STUDY OF THREE-DIMENSIONAL 
FLOW EFFECTS. Warren J. Whitney, Warner L. 
Stewart, and Harold J. Schum. May 1953. 20p. 
diagrs., photo., tab. (NACA RM E53C02) 



INVESTIGATION OF TURBINES FOR DRIVING 
SUPERSONIC COMPRESSORS. V - DESIGN AND 
PERFORMANCE OF THIRD CONFIGURATION WITH 
NONTWISTED ROTOR BLADES. Warren J. 
Whitney, Warner L. Stewart, and Daniel E. Monroe. 
September 1953. 23p. diagrs., photos., tab. 
(NACA RM E53G27) 



EFFECT OF NOZZLE SECONDARY FLOWS ON 
TURBINE PERFORMANCE AS INDICATED BY EXIT 
SURVEYS OF A ROTOR. Warren J. Whitney, 
Howard A. Buckner, Jr., and Daniel E. Monroe. 
April 1954. lip. diagrs. (NACA RM E54B03) 



QUALITATIVE STUDY OF FLOW CHARACTERIS- 
TICS THROUGH SINGLE-STAGE TURBINES AS 
MADE FROM ROTOR-EXIT SURVEYS. Robert Y. 
Wong, James W. Miser, and Warner L. Stewart. 
March 1956. 26 p. diagrs. (NACA RM E55K21) 



232 



(3) PROPULSION 



(3.7.2) 
COOLING 



A TWO-DIMENSIONAL CASCADE STUDY OF THE 
AERODYNAMIC CHARACTERISTICS OF A 
TURBINE-ROTOR BLADE SUITABLE FOR AIR 
COOLING. Henry W. Plohr and Cavour H. Hauser. 
September 1951. 15p. diagrs., photos. 
(NACA RM E51G18) 



COLD-AIR INVESTIGATION OF A TURBINE WITH 
NONTWISTED ROTOR BLADES SUITABLE FOR AIR 
COOLING. Thomas R. Heaton, William R. Slivka, 
and Leonard F. Westra. March 1952. 34p. diagrs., 
photos. (NACA RM E52A25) 



AN EXPERIMENTAL CASCADE STUDY OF THE 
EFFECTS OF A SOLIDITY REDUCTION ON THE 
TWO-DIMENSIONAL AERODYNAMIC CHARACTER- 
ISTICS OF A TURBINE-ROTOR BLADE SUITABLE 
FOR AIR COOLING. Henry W. Plohr and William J. 
Nusbaum. May 1952. 17p. diagrs., photos. 
(NACA RM E52B27) 



AN ANALYTICAI METHOD FOR EVALUATING 
FACTORS AFFE^ TING APPLICATION OF TRAN- 
SPIRATION COCKING TO GAS TURBINE BLADES. 
Jack B. Es^ar. September 1952. ii, 68p. diagrs., 
tabs. (NACA RM E52G01) 



ANALYTICAL COMPARISON OF TURBINE -BLADE 
COOLING SYSTEMS DESIGNED FOR A TURBOJET 
ENGINE OPERATING AT SUPERSONIC SPEED AND 
HIGH ALTITUDE. I - LIQUID -COO LING SYSTEMS. 
Wilson B. Schramm, Alfred J. Nachtigall, and 
Vernon L. Arne. January 1953. 52p. diagrs., 
tabs. (NACA RM E52J29) 



ANALYTICAL COMPARISON OF TURBINE-BLADE 
COOLING SYSTEMS DESIGNED FOR A TURBOJET 
ENGINE OPERATING AT SUPERSONIC SPEED AND 
HIGH ALTITUDE. H - AIR-COOLING SYSTEMS. 
Wilson B. Schramm, Vernon L. Arne, and Alfred J. 
Nachtigall. January 1953. 50p. diagrs., tabs. 
(NACARM E52J30) 



INVESTIGATION OF WATER-SPRAY COOLING OF 
TURBINE BLADES IN A TURBOJET ENGINE. 
John C. Freche and William J. Stelpflug. March 
1953. 45p. diagrs., photos., tab. 
(NACA RM E53A23) 



MECHANICAL DESIGN ANALYSIS OF SEVERAL 
NONCRITICAL AIR-COOLED TURBINE DISKS AND 
A CORRUGATED -INSERT AIR-COOLED TURBINE 
ROTOR BLADE. Merland L. Moseson, Morton H. 
Krasner, and Robert R. Ziemer. July 1953. 49p. 
diagrs., photos., tabs. (NACARM E53E21) 



EXPERIMENTAL INVESTIGATION OF SEVERAL 
WATER-INJECTION CONFIGURATIONS FOR 
TURBINE-BLADE SPRAY COOLING IN A TURBOJET 
ENGINE. John C. Freche and Roy A. McKinnon. 
October 1953. 37p. photos., diagrs., tabs. 
(NACA RM E53H06) 



EVALUATION OF EFFECTS OF RANDOM PERMEA- 
BILITY VARIATIONS ON TRANSPIRATION -COOLED 
SURFACES. Jack B. Esgar and Hadley T. Richards. 
November 1953. 59p. diagrs., photos. 
(NACA RM E53G16) 



ANALYSIS OF FACTORS AFFECTING SELECTION 
AND DESIGN OF AIR-COOLED SINGLE-STAGE 
TURBINES FOR TURBOJET ENGINES. I - TUR- 
BINE PERFORMANCE AND ENGINE WEIGHT-FLOW 
CAPACITY. Richard J. Rossbach, Wilson B. 
Schramm, and James E. Hubbartt. May 1954. 50p. 
diagrs., tab. (NACA RM E54C22) 



ANALYSIS OF FACTORS AFFECTING SELECTION 
AND DESIGN OF AIR-COOLED SINGLE-STAGE 
TURBINES FOR TURBOJET ENGINES. II - 

ANALYTICAL TECHNIQUES. Richard J. Rossbach. 
June 1954. 29p. diagrs. (NACA RM E54D21) 



DESIGN AND EXPERIMENTAL INVESTIGATION OF 
LIGHTWEIGHT BASES FOR AIR-COOLED TURBINE 
ROTOR BLADES. John C. Freche and Roy A 
McKinnon. July 1954. 27p. diagrs., photos., tab. 
(NACA RM E54E10) 



ANALYSIS OF FACTORS AFFECTING SELECTION 
AND DESIGN OF AIR-COOLED SINGLE-STAGE 
TURBINES FOR TURBOJET ENGINES. Ill - 
ENGINE DESIGN-POINT PERFORMANCE. James 
E. Hubbartt, Richard J. Rossbach, and Wilson B. 
Schramm. September 1954. 41p. diagrs., tab. 
(NACA RM E54F16a) 



ANALYSIS OF FACTORS AFFECTING SELECTION 
AND DESIGN OF AIR-COOLED SINGLE-STAGE 
TURBINES FOR TURBOJET ENGINES. IV - 
COOLANT-FLOW REQUIREMENTS AND PER- 
FORMANCE OF ENGINES USING AIR-COOLED 
CORRUGATED-INSERT BLADES. Henry O. Slone 
and James E. Hubbartt. May 1955. 45p. diagrs., 
photos., tab. (NACA RM E55C09) 



PRELIMINARY INVESTIGATION OF HOLLOW- 
BLADED TURBINES HAVING CLOSED AND OPEN 
BLADE TIPS- Gordon T. Smith and Robert O. 
Hickel. August 1955. 18p. diagrs., photo., tab. 
(NACARM E55F27a) 



ANALYTICAL COMPARISON OF CONVECTION- 
COOLED TURBINE BLADE COOLING-AIR RE- 
QUIREMENTS FOR SEVERAL RADIAL GAS- 
TEMPERATURE PROFILES. James E. Hubbartt 
and Henry O. Slone. September 1955. 46d. diagrs. 
(NACA RM E55G14) 



FABRICATION AND ENDURANCE OF AIR-COOLED 
STRUT -SUPPORTED TURBINE BLADES WITH 
STRUTS CAST OF X-40 ALLOY. Eugene F. Schum, 
Francis S. Stepka, and Robert E. Oldrieve. April 
1956. 39p. diagrs., photos., tabs. 
(NACA RM E56A12) 



FABRICATION TECHNIQUES AND HEAT-TRANSFER 
RESULTS FOR CAST-CORED AIR-COOLED TUR- 
BINE BLADES. John C. Freche and Robert E. 
Oldrieve. June 1956. 35p. diagrs., photos. 
(NACA RM E56C06) 



VISUALIZATION OF ROTOR TD? SECONDARY 
FLOWS WITH BLADE TIP AIR DISCHARGE AND 
SUCTION IN A LOW -SPEED TURBINE . Milton G . 
Kofskey and Hubert W. Allen. August 1956. 28p. 
diagrs., photos. (NACARM E56E16) 



THERMODYNAMIC STUDY OF AIR-CYCLE AND 
MERCURY -VAPOR-CYCLE SYSTEMS FOR REFRIG- 
ERATING COOLING AIR FOR TURBINES OR OTHER 
COMPONENTS. Alfred J. Nachtigall, John C. 
Freche, and Jack B. Esgar. October 1956. 47p. 
diagrs. (NACA RM E56G13) 



(3) PROPULSION 



233 



EXPERIMENTAL INVESTIGATION OF MODIFIED 
CAST-CORED BLADES HAVING HOLLOW TIP 
SECTIONS. Robert E. Oldrieve and John C. 
Free he, June 1957. 36p. diagrs.. Dhotos., 
(NACA RM E57C15) 



VELOCITY AND FRICTION CHARACTERISTICS OF 
LAMINAR VISCOUS BOUNDARY- LAYER AND 
CHANNEL FLOW OVER SURFACES WITH EJEC- 
TION OR SUCTION. E. R. G. Eckert, Patrick L. 
Donoughe and Betty Jo Moore. December 1957. 
57p. diagrs., taba. (NACA TN 4102) 



EFFECT OF CHORD SIZE ON WEIGHT AND COOL- 
ING CHARACTERISTICS OF AIR-COOLED TURBINE 
BLADES. Jack B. Esgar, Eugene F. Schum, and 
Arthur N. Curren. 1958. ii, 13p. diagrs., tabs. 
(NACA Rept. 1354. Supersedes TN 3923) 



ON PAIRS OF SOLUTIONS OF A CLASS OF INTER- 
NAL VISCOUS FLOW PROBLEMS WITH BODY 
FORCES. Simon Ostrach and Lynn U. Albers. 
June 1958. 21p. diagrs., tabs. (NACA TN 4273) 



VIBRATION SURVEY OF FOUR REPRESENTATIVE 
TYPES OF AIR-COOLED TURBINE BLADES. 
Howard F. Calvert and Gordon T. Smith. July 1958. 
22p. diagrs., photos., tabs. (NACA TN 4100) 



NATURAL CONVECTION INSIDE A FLAT ROTATING 
CONTAINER. Simon Ostrach and Willis H. Braun. 
September 1958. 27p. diagrs. (NACA TN 4323) 



(3.7.3) 
STRESS AND VIBRATION 



MECHANICAL DESIGN ANALYSIS OF SEVERAL 
NONCRITICAL AIR-COOLED TURBINE DISKS AND 
A CORRUGATED-INSERT AIR-COOLED TURBINE 
ROTOR BLADE. MerlandL. Moseson, Morton H. 
Krasner, and Robert R. Ziemer. July 1953. 49p. 
diagrs., photos., tabs. (NACA RM E53E21) 



DESIGN AND EXPERIMENTAL INVESTIGATION OF 
LIGHTWEIGHT BASES FOR AIR-COOLED TURBINE 
ROTOR BLADES John C. Freche and Roy A. 
Mi-Kmnon. July 1954. 27p. diagrs., photos., tab. 
(NACA RM E54EI0) 



FACTORS THAT AFFECT OPERATIONAL RELI- 
ABILITY OF TURBOJET ENGINES. Lewis 
Laboratory Staff. January 1956. 376p. diagrs., 
photos., tabs. (NACA RM E55H02) 



FABRICATION AND ENDURANCE OF AIR-COOLED 
STRUT -SUPPORTED TURBINE BLADES WITH 
STRUTS CAST OF X-40 ALLOY. Eugene F. Schum, 
Francis S. Stepka, and Robert E. Oldrieve. April 
1956. 39p. diagrs., photos., tabs. 
(NACA RM EFi6A12) 



APPLICATION OF A HIGH-TEMPERATURE STATIC 
STRAIN GAGE TO THE MEASUREMENT OF THER- 
MAL STRESSES IN A TURBINE STAT OR VANE. 
R. H. Kemp, C. R. Morse, and M. H. Hlrschberg. 
March 1958. 36p. diagrs., photos., tab. 
(NACA TN 4215) 



VIBRATION SURVEY OF FOUR REPRESENTATIVE 
TYPES OF AIR-COOLED TURBINE BLADES. 
Howard F. Calvert and Gordon T. Smith. July 1958. 
22p. diagrs., photos., tabs. (NACA TN 4100) 



THEORETICAL AND EXPERIMENTAL ANALYSIS OF 
THE REDUCTION OF ROTOR BLADE VIBRATION IN 
TURBOMACHINERY THROUGH THE USE OF MODI- 
FIED STATOR VANE SPACING. Richard H. Kemp, 
Marvin H. Hirschberg, and William C. Morgan. 
September 1958. 43p. diagrs., photos., tabs. 
(NACA TN 4373) 



(3.7.4) 
MATCHING 



TURBINE DESIGN CONSIDERATIONS FOR 
TURBINE -PROPELLER ENGINE OPERATING OVER 
A RANGE OF FLIGHT CONDITIONS. Elmer H. 
Davison. June 1953. 20p. diagrs., tab. 
(NACA RM E53D16) 



TURBOPROP-ENGINE DESIGN CONSIDERATIONS. 
I - EFFECT OF MODE OF ENGINE OPERATION ON 
PERFORMANCE OF TURBOPROP ENGINE WITH 
CURRENT COMPRESSOR PRESSURE RATIO. 
Elmer H. Davison. May 1955. 34p. diagrs. 
(NACARME54D19) 



TURBOPROP -ENGINE DESIGN CONSIDERATIONS, 
n - DESIGN REQUIREMENTS AND PERFORMANCE 
OF TURBOPROP ENGINES WITH A SINGLE -SPOOL 
HIGH -PRESSURE -RATIO COMPRESSOR. Elmer H. 
Davison and Margaret C. Stall a. May 1955. 32p. 
diagrs., tabs. (NACA RM E55B18) 



EFFECT OF DESIGN OVER-ALL COMPRESSOR 
PRESSURE RATIO DIVISION ON ACCELERATION 
CHARACTERISTICS OF THREE HYPOTHETICAL 
TWO-SPOOL TURBOJET ENGINES. Richard E. 
Filippi and James F. Dugan, Jr. August 1956. 26p. 
diagrs. (NACA RM E56D13) 



234 



(3) PROPULSION 



(3.8) 
Friction and Lubrication 



(3.8.1) 
THEORY AND EXPERIMENT 



BONDED LEAD MONOXIDE FILMS AS SOLID 
LUBRICANTS FOR TEMPERATURES UP TO 
1250° F. Harold E. SLiney and Robert L. Johnson. 
May 1957. 25p. diagrs., photos., tabs. 
(NACA RM E57B15) 



FRICTION STUDIES OF VARIOUS MATERIALS IN 
LIQUID NITROGEN, D. W. Wisander, W. F. Hady, 
andR. L. Johnson. February 1958. 35p. diagrs., 
photos., tab. (NACA TN 4211) 



RELATION OF JOURNAL BEARING PERFORMANCE 
TO MINIMUM OIL -FILM THICKNESS. F. W. Ocvirk 
andG. B. DuBois, Cornell University. April 1958. 
48p. diagrs., tab. (NACA TN 4223) 



FRICTION AND WEAR WITH REACTIVE GASES AT 
TEMPERATURES UP TO 1200° F. Gordon P. Allen, 
Donald H. Buckley, and Robert L. Johnson. 
September 1958. 26p. diagrs., photos. 
(NACA TN 4316) 



(3.8.1. 1) 
HYDRODYNAMIC THEORY 



AN ANALYSIS OF THE EFFECT OF SEVERAL 
PARAMETERS ON THE STABILITY OF AN AIR- 
LUBRICATED HYDROSTATIC THRUST BEARING. 
William H. Roudebush. October 1957. 34p. diagrs., 
tab. (NACA TN 4095) 



EFFECT OF LUBRICANT VISCOSITY ON ROLLING- 
CONTACT FATIGUE LIFE. Thomas L. Carter. 
October 1957. 25p. diagrs., photo., tabs. 
(NACA TN4101) 



EFFECT OF TEMPERATURE ON ROLLING- 
CONTACT FATIGUE LIFE WITH LIQUID AND DRY 
POWDER LUBRICANTS. Thomas L. Carter. 
January 1958. 40p. diagrs., photos., tabs. 
(NACA TN 4163) 



EFFECT OF LUBRICANT BASE STOCK ON 
ROLLING-CONTACT FATIGUE LIFE. Thomas L. 
Carter. February 1958. 28p. diagrs., tab. 
(NACA TN 4161) 



PRELIMINARY STUDIES OF ROLLING-CONTACT 
FATIGUE LIFE OF HIGH-TEMPERATURE BEARING 
MATERIALS. Thomas L. Carter. April 1958. 
27p. diagrs., tab. (NACA RM E57K12) 



(3.8. 1.2) 

CHEMISTRY OF LUBRICATION 



BONDED LEAD MONOXIDE FILMS AS SOLID 
LUBRICANTS FOR TEMPERATURES UP TO 
1250° F. Harold E. SUney and Robert L. Johnson. 
May 1957. 25p. diagrs., photos., tabs. 
(NACA RM E57B15) 



EFFECT OF SLIDING VELOCITY ON FRICTION 
PROPERTIES AND ENDURANCE LIFE OF BONDED 
LEAD MONOXIDE COATINGS AT TEMPERATURES 
UP TO 1250° F. Harold E. Sliney. May 1958. 
15p. diagrs. (NACA RM E58B11) 



FRICTION AND WEAR WITH REACTIVE GASES AT 
TEMPERATURES UP TO 1200° F. Gordon P. Allen, 
Donald H, Buckley, and Robert L. Johnson. 
September 1958. 26p. diagrs., photos. 
(NACA TN 4316) 



(3.8.2) 
SLIDING CONTACT SURFACES 



RELATION OF JOURNAL BEARING PERFORMANCE 
TO MINIMUM OIL -FILM THICKNESS. F. W. Ocvirk 
andG. B. DuBois, Cornell University. April 1958. 
48p. diagrs., tab. (NACA TN 4223) 



(3.8.3) 
ROLLING CONTACT SURFACES 



FACTORS THAT AFFECT OPERATIONAL RELI- 
ABILITY OF TURBOJET ENGINES. Lewis 
Laboratory Staff. January 1956. 376p. diagrs., 
photos., tabs. (NACA RM E55H02) 



EFFECT OF LUBRICANT VISCOSITY ON ROLLING- 
CONTACT FATIGUE LIFE. Thomas L. Carter. 
October 1957. 25p. diagrs., photo., tabs. 
(NACA TN 4101) 



EFFECT OF TEMPERATURE ON ROLLING- 
CONTACT FATIGUE LIFE WITH LIQUID AND DRY 
POWDER LUBRICANTS. Thomas L. Carter. 
January 1958. 40p. diagrs., photos., tabs. 
(NACA TN 4163) 



EFFECT OF LUBRICANT BASE STOCK ON 
ROLLING-CONTACT FATIGUE LIFE. Thomas L. 
Carter- February 1958. 28p. diagrs., tab. 
(NACA TN 4161) 



EFFECT OF FIBER ORIENTATION IN RACES AND 
BALLS UNDER ROLLING -CONTACT FATIGUE CON- 
DITIONS. Thomas L. Carter. February 1958. 
37p. diagrs., photos., tabs. (NACA TN 4216) 

PRELIMINARY STUDIES OF ROLLING -CONTACT 
FATIGUE LIFE OF HIGH-TEMPERATURE BEARING 
MATERIALS. Thomas L. Carter. April 1958. 
27p. diagrs,, tab. (NACA RM E57K12) 



(3.8.3. 1) 
ANTIFRICTION BEARING 



EFFECT OF TEMPERATURE ON ROLLING- 
CONTACT FATIGUE LIFE WITH LIQUID AND DRY 
POWDER LUBRICANTS. Thomas L- Carter. 
January 1958. 40p. diagrs., photos., tabs. 
(NACA TN 4163) 



(3) PROPULSION 



235 



EFFECT OF LUBRICANT BASE STOCK ON 
ROLLING -CON TACT FATIGUE LIFE. Thomas L. 
Carter. February 1958. 28p. diagrs., tab. 
(NACA TN 4161) 



EFFECT OF FIBER ORIENTATION IN RACES AND 
BALLS UNDER ROLLING-CONTACT FATIGUE CON- 
DITIONS. Thomas L. Carter. February 1958. 
37p. diagrs., photos., tabs. {NACA TN 4216) 



PRELIMINARY STUDIES OF ROLLING-CONTACT 
FATIGUE LIFE OF HIGH-TEMPERATURE BEARING 
MATERIALS. Thomas L. Carter. April 1958. 
27p. diagrs., tab. (NACA RM E57K12) 



(3.8.4) 

SLIDING AND ROLLING 

CONTACT SURFACES 



FACTORS THAT AFFECT OPERATIONAL RELI- 
ABILITY OF TURBOJET ENGINES. Lewis 
Laboratory Staff . January 1956. 376p. diagrs., 
photos., tabs. (NACA RM E55H02) 



(3.8.5) 
LUBRICANTS 



BONDED LEAD MONOXIDE FILMS AS SOLID 

LUBRICANTS FOR TEMPERATURES UP TO 

J 250° F. Harold E. Sliney and Robert L. Johnson. 

May 1957, 25p. diagrs., photos., tabs. 

(NACA RM E57B15) 



AN ANALYSIS OF THE EFFECT OF SEVERAL 
PARAMETERS ON THE STABILITY OF AN AIR- 
LUBRICATED HYDROSTATIC THRUST BEARING. 
William H. Roudebush. October 1957. 34p. diagrs., 
tab. (NACA TN 4095) 



EFFECT OF LUBRICANT VISCOSITY ON ROLLING- 
CONTACT FATIGUE LIFE. Thomas L. Carter. 
October 1957. 25p. diagrs., photo., tabs. 
(NACA TN 4101) 



EFFECT OF TEMPERATURE ON ROLLING - 
CONTACT FATIGUE LIFE WITH LIQUID AND DRY 
POWDER LUBRICANTS. Thomas L. Carter. 
January 1958. 40p. diagrs., photos., tabs. 
(NACA TN 4163) 



EFFECT OF LUBRICANT BASE STOCK ON 
ROLLING-CONTACT FATIGUE LIFE. Thomas L. 
Carter. February 1958. 28p. diagrs., tab. 
(NACA TN 4161) 



EFFECT OF SLIDING VELOCITY ON FRICTION 
PROPERTIES AND ENDURANCE LIFE OF BONDED 
LEAD MONOXIDE COATINGS AT TEMPERATURES 
UP TO 1250° F. Harold E. Sliney. May 1958. 
15p, diagrs. (NACA RM E58B11) 



RESULTS OF AN EXPERIMENTAL INVESTIGATION 
OF SMALL VISCOUS DAMPERS. Milton A. Silveira, 
Domenic J. Maglieri, and George W. Brooks. June 
1958. 49p. diagrs., photos. (NACA TN 4257)-- 



FRICTION AND WEAR WITH REACTIVE GASES AT 
TEMPERATURES UP TO 1200° F. Gordon P. Allen, 
Donald H. Buckley, and Robert L. Johnson. 
September 1958. 26p. diagrs., photos. 
(NACA TN 4316) 



236 



(3) PROPULSION 



(3.9) 
Heat Transfer 



ANALYTICAL COMPARISON OF TURBINE-BLADE 
COOLING SYSTEMS DESIGNED FOR A TURBOJET 
ENGINE OPERATING AT SUPERSONIC SPEED AND 
HIGH ALTITUDE . I - LIQUID -COO LING SYSTEMS. 
Wilson B. Schramm, Alfred J. Nachtigall, and 
Vernon L. Arne. January 1953. 52p. diagrs., 
tabs. (NACARM E52J 29) 



ANALYTICAL COMPARISON OF